diff --git a/.github/workflows/integrationtests.yml b/.github/workflows/integrationtests.yml index ae144e1f2..087a3e4b6 100644 --- a/.github/workflows/integrationtests.yml +++ b/.github/workflows/integrationtests.yml @@ -60,6 +60,10 @@ jobs: shell: bash -l {0} run: installation/Ubuntu/install_sumo.sh + - name: Install AVL + shell: bash -l {0} + run: installation/Ubuntu/install_pyavl.sh + - name: Install SU2 shell: bash -l {0} run: installation/Ubuntu/install_su2.sh diff --git a/CONTRIBUTING.md b/CONTRIBUTING.md index cec871a56..829e163dd 100644 --- a/CONTRIBUTING.md +++ b/CONTRIBUTING.md @@ -178,7 +178,11 @@ Other resources that could the useful. #### SUMO -- [SUMO website](https://www.larosterna.com/products/open-source) +- [SUMO website](https://www.larosterna.com/oss/) + +#### AVL + +- [AVL website](https://web.mit.edu/drela/Public/web/avl/) #### SU2 diff --git a/README.md b/README.md index b117f0fb2..08c1eaedf 100644 --- a/README.md +++ b/README.md @@ -79,7 +79,7 @@ Follow the [test cases](#test-cases) to discover the different way of using CEAS ```mermaid graph LR; - PyTornado-->SaveAeroCoefficients; + PyAVL-->SaveAeroCoefficients; ``` @@ -134,6 +134,7 @@ warning: : The module does not work completely as expected. It is not a bug, but - [CLCalculator](ceasiompy/CLCalculator/README.md) :heavy_check_mark: - [PyTornado](ceasiompy/PyTornado/README.md) :heavy_check_mark: +- [PyAVL](ceasiompy/PyAVL/README.md) :heavy_check_mark: - [SU2Run](ceasiompy/SU2Run/README.md) :heavy_check_mark: - [SkinFriction](ceasiompy/SkinFriction/README.md) :heavy_check_mark: - [SaveAeroCoefficients](ceasiompy/SaveAeroCoefficients/README.md) :heavy_check_mark: diff --git a/ceasiompy/PyAVL/README.md b/ceasiompy/PyAVL/README.md new file mode 100644 index 000000000..99493d12d --- /dev/null +++ b/ceasiompy/PyAVL/README.md @@ -0,0 +1,68 @@ + + + +# PyAVL + +**Categories:** Aerodynamics, vortex lattice method, low-fidelity. + +**State**: :heavy_check_mark: + + + +`PyAVL` module is a launcher for the [Athena Vortex Lattice (AVL)](https://web.mit.edu/drela/Public/web/avl/) solver, developed by M. Drela and H. Youngren at MIT. It is a vortex lattice method (VLM) solver for low-fidelity aerodynamic computations. + +## Inputs + +`PyAVL` takes as input a CPACS file, the aircraft geometry is read to create the VLM model for the wings and fuselage. The flight conditions have to be defined within an aeromap, as well as the number of vortex panels to use. + +

+ +

+

+Example of AVL geometry model. +

+ +## Analyses + +`PyAVL` computes the aerodynamic coefficients of an aircraft for a given aeromap and writes the results in a CPACS file. It calculates the total forces on the aircraft, the forces on individual surfaces, the forces on wing strips, and the forces on each panel. The stability derivatives can also be computed. + +## Outputs + +`PyAVL` outputs a CPACS file with the aerodynamic coefficients added in the aeromap. The settings of the simulation (number of chordwise/spanwise vortices, vortex distribution) are saved. The following force files are saved: +- `ft.txt`: Total Forces. +- `fn.txt`: Surface Forces. +- `fs.txt`: Strip Forces. +- `fe.txt`: Element Forces (vortex strength). + +The following plots are generated: +- `plot.pdf`: it contains a plot of the initial AVL geometry model, and a plot with the aerodynamic loads on the aircraft. +- `lift_distribution.png`: plot of the lift distribution along the span. + +

+ +

+

+Example of aerodynamic loads computed by AVL. +

+ + +## Installation or requirements + +Following the automatic installation procedure on the [CEASIOMpy installation page](../../installation/INSTALLATION.md) should install `PyAVL` automatically with the other tools. + +## Limitations + +`PyAVL` uses a Vortex Lattice Method solver: +- The flow is quasi-steady and ideal: incompressible, irrotational, and inviscid. +- The flow is low-subsonic: [Prandlt-Glauert transformation](https://en.wikipedia.org/wiki/Prandtl%E2%80%93Glauert_transformation) is used to adapt the equations up to Mach 0.6. +- Lifting surfaces are assumed to be thin, the thickness is not taken into account. +- The angle of attack and sideslip must be small. +- Viscous effects, turbulence or boundary layer phenomena are not solved at all. + +## More information + +- [AVL documentation.](https://web.mit.edu/drela/Public/web/avl/AVL_User_Primer.pdf) +- [AVL website.](https://web.mit.edu/drela/Public/web/avl/) +- [Flight Vehicule Aerodynamics](https://mitpress.mit.edu/9780262526449/flight-vehicle-aerodynamics/) by M. Drela. +- [Low-Speed Aerodynamics](https://www.cambridge.org/core/books/lowspeed-aerodynamics/077FAF851C4582F1B7593809752C44AE) by J. Katz and A. Plotkin. +- [Aerodynamics for Engineers](https://www.cambridge.org/highereducation/books/aerodynamics-for-engineers/C8AAC9F38F0781CA38AB65FA85E61CCF#overview) by J. Bertin. diff --git a/ceasiompy/PyAVL/__init__.py b/ceasiompy/PyAVL/__init__.py new file mode 100644 index 000000000..e69de29bb diff --git a/ceasiompy/PyAVL/__specs__.py b/ceasiompy/PyAVL/__specs__.py new file mode 100644 index 000000000..3dc0f8093 --- /dev/null +++ b/ceasiompy/PyAVL/__specs__.py @@ -0,0 +1,118 @@ +from ceasiompy.utils.moduleinterfaces import CPACSInOut +from ceasiompy.utils.commonxpath import ( + CEASIOMPY_XPATH, + AVL_PLOT_XPATH, + AVL_VORTEX_DISTR_XPATH, + AVL_FUSELAGE_XPATH, + AVL_AEROMAP_UID_XPATH, + AEROPERFORMANCE_XPATH, +) +from pathlib import Path + +# ===== Module Status ===== +# True if the module is active +# False if the module is disabled (not working or not ready) +module_status = True # Because it is just an example not a real module + +# ===== Results directory path ===== + +RESULTS_DIR = Path("Results", "PyAVL") + +# ===== CPACS inputs and outputs ===== + +cpacs_inout = CPACSInOut() + +# ----- Input ----- + +# * In the following example we add three (!) new entries to 'cpacs_inout' +# * Try to use (readable) loops instead of copy-pasting three almost same entries :) +cpacs_inout.add_input( + var_name="aeromap_uid", + var_type=list, + default_value=None, + unit=None, + descr="Name of the aero map to calculate", + xpath=AVL_AEROMAP_UID_XPATH, + gui=True, + gui_name="__AEROMAP_SELECTION", + gui_group="Aeromap settings", +) + +cpacs_inout.add_input( + var_name="integrate_fuselage", + var_type=bool, + default_value=False, + unit=None, + descr="Select to integrate the fuselage in the AVL model", + xpath=AVL_FUSELAGE_XPATH, + gui=True, + gui_name="Integrate fuselage", + gui_group="Fuselage", +) + +cpacs_inout.add_input( + var_name="panel_distribution", + var_type=list, + default_value=["cosine", "sine", "equal"], + unit=None, + descr=("Select the type of distribution"), + xpath=AVL_VORTEX_DISTR_XPATH + "/Distribution", + gui=True, + gui_name="Choice of distribution", + gui_group="Vortex Lattice Spacing Distributions", +) + +cpacs_inout.add_input( + var_name="chordwise_vort", + var_type=int, + default_value=20, + unit=None, + descr="Select the number of chordwise vortices", + xpath=AVL_VORTEX_DISTR_XPATH + "/Nchordwise", + gui=True, + gui_name="Number of chordwise vortices", + gui_group="Vortex Lattice Spacing Distributions", +) + +cpacs_inout.add_input( + var_name="spanwise_vort", + var_type=int, + default_value=50, + unit=None, + descr="Select the number of spanwise vortices", + xpath=AVL_VORTEX_DISTR_XPATH + "/Nspanwise", + gui=True, + gui_name="Number of spanwise vortices", + gui_group="Vortex Lattice Spacing Distributions", +) + +cpacs_inout.add_input( + var_name="save_plots", + var_type=bool, + default_value=False, + unit=None, + descr="Select to save geometry and results plots", + xpath=AVL_PLOT_XPATH, + gui=True, + gui_name="Save plots", + gui_group="Plots", +) + +# ----- Output ----- + +cpacs_inout.add_output( + var_name="output", + default_value=None, + unit="1", + descr="Description of the output", + xpath=CEASIOMPY_XPATH + "/test/myOutput", +) + +cpacs_inout.add_output( + var_name="aeromap_avl", # name to change... + # var_type=CPACS_aeroMap, # no type pour output, would it be useful? + default_value=None, + unit="-", + descr="aeroMap with aero coefficients calculated by AVL", + xpath=AEROPERFORMANCE_XPATH + "/aeroMap/aeroPerformanceMap", +) diff --git a/ceasiompy/PyAVL/avlrun.py b/ceasiompy/PyAVL/avlrun.py new file mode 100644 index 000000000..f866f5f98 --- /dev/null +++ b/ceasiompy/PyAVL/avlrun.py @@ -0,0 +1,129 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Script to run AVL calculations in CEASIOMpy. +AVL allows to perform aerodynamic analyses using +the vortex-lattice method (VLM) + +Python version: >=3.8 + +| Author: Romain Gauthier +| Creation: 2024-03-14 + +TODO: + + * Things to improve ... + +""" + +# ============================================================================== +# IMPORTS +# ============================================================================== +from ceasiompy.utils.ceasiomlogger import get_logger +from ceasiompy.utils.moduleinterfaces import get_toolinput_file_path, get_tooloutput_file_path +from ceasiompy.PyAVL.func.cpacs2avl import convert_cpacs_to_avl +from ceasiompy.PyAVL.func.avlconfig import ( + write_command_file, + get_aeromap_conditions, + get_option_settings, +) +from ceasiompy.PyAVL.func.avlresults import get_avl_results +from ceasiompy.utils.ceasiompyutils import get_results_directory + +import subprocess +from pathlib import Path +from ambiance import Atmosphere + + +log = get_logger() + +MODULE_DIR = Path(__file__).parent +MODULE_NAME = MODULE_DIR.name + +# ================================================================================================= +# CLASSES +# ================================================================================================= + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= +def run_avl(cpacs_path, wkdir): + """Function to run AVL. + + Function 'run_avl' runs AVL calculations using a CPACS file + as input. + + Args: + cpacs_path (Path) : path to the CPACS input file + wkdir (Path) : path to the working directory + """ + + alt_list, mach_list, aoa_list, aos_list = get_aeromap_conditions(cpacs_path) + save_fig, _, _, _, _ = get_option_settings(cpacs_path) + + for i_case in range(len(alt_list)): + alt = alt_list[i_case] + mach = mach_list[i_case] + aoa = aoa_list[i_case] + aos = aos_list[i_case] + Atm = Atmosphere(alt) + + density = Atm.density[0] + velocity = Atm.speed_of_sound[0] * mach + g = Atm.grav_accel[0] + + case_dir_name = ( + f"Case{str(i_case).zfill(2)}_alt{alt}_mach{round(mach, 2)}" + f"_aoa{round(aoa, 1)}_aos{round(aos, 1)}" + ) + + Path(wkdir, case_dir_name).mkdir(exist_ok=True) + case_dir_path = Path(wkdir, case_dir_name) + + avl_path = convert_cpacs_to_avl(cpacs_path, wkdir=case_dir_path) + + command_path = write_command_file( + avl_path, + case_dir_path, + save_plots=save_fig, + alpha=aoa, + beta=aos, + mach_number=mach, + ref_velocity=velocity, + ref_density=density, + g_acceleration=g, + ) + + subprocess.run(["xvfb-run", "avl"], stdin=open(str(command_path), "r"), cwd=case_dir_path) + + if save_fig: + if not Path(case_dir_path, "plot.ps").exists(): + raise FileNotFoundError("File 'plot.ps' does not exist.") + + subprocess.run(["ps2pdf", "plot.ps", "plot.pdf"], cwd=case_dir_path) + subprocess.run(["rm", "plot.ps"], cwd=case_dir_path) + + +# ================================================================================================= +# MAIN +# ================================================================================================= + + +def main(cpacs_path, cpacs_out_path): + log.info("----- Start of " + MODULE_NAME + " -----") + + results_dir = get_results_directory("PyAVL") + run_avl(cpacs_path, results_dir) + get_avl_results(cpacs_path, cpacs_out_path, results_dir) + + log.info("----- End of " + MODULE_NAME + " -----") + + +if __name__ == "__main__": + cpacs_path = get_toolinput_file_path(MODULE_NAME) + cpacs_out_path = get_tooloutput_file_path(MODULE_NAME) + + main(cpacs_path, cpacs_out_path) diff --git a/ceasiompy/PyAVL/files/avl_example.png b/ceasiompy/PyAVL/files/avl_example.png new file mode 100644 index 000000000..ee2134d02 Binary files /dev/null and b/ceasiompy/PyAVL/files/avl_example.png differ diff --git a/ceasiompy/PyAVL/files/avl_example_loads.png b/ceasiompy/PyAVL/files/avl_example_loads.png new file mode 100644 index 000000000..6fdc182b9 Binary files /dev/null and b/ceasiompy/PyAVL/files/avl_example_loads.png differ diff --git a/ceasiompy/PyAVL/files/avl_logo.png b/ceasiompy/PyAVL/files/avl_logo.png new file mode 100644 index 000000000..0c1551049 Binary files /dev/null and b/ceasiompy/PyAVL/files/avl_logo.png differ diff --git a/ceasiompy/PyAVL/files/template.mass b/ceasiompy/PyAVL/files/template.mass new file mode 100644 index 000000000..9faeeb38e --- /dev/null +++ b/ceasiompy/PyAVL/files/template.mass @@ -0,0 +1,19 @@ +#------------------------------------------------- +# N+3 Config D8-1 +# +# Dimensional unit and parameter data. +# Mass & Inertia breakdown. +#------------------------------------------------- + +# Names and scalings for units to be used for trim and eigenmode calculations. +# The Lunit and Munit values scale the mass, xyz, and inertia table data below. +# Lunit value will also scale all lengths and areas in the AVL input file. +Lunit = 1.0 m +Munit = 1.0 kg +Tunit = 1.0 s + +#------------------------- +# Gravity and density to be used as default values in trim setup. +# Must be in the units given above. +g = 9.81 +rho = 1.2 diff --git a/ceasiompy/PyAVL/func/avlconfig.py b/ceasiompy/PyAVL/func/avlconfig.py new file mode 100644 index 000000000..555b27a56 --- /dev/null +++ b/ceasiompy/PyAVL/func/avlconfig.py @@ -0,0 +1,231 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Script to get the flight conditions (alt, aoa, mach...) from +the input CPACS file, and write the command file for AVL. + +Python version: >=3.8 + +| Author: Romain Gauthier +| Creation: 2024-03-14 + +TODO: + + * Things to improve... + +""" + +# ============================================================================== +# IMPORTS +# ============================================================================== + +from pathlib import Path + +from ceasiompy.utils.ceasiomlogger import get_logger +from ceasiompy.utils.commonxpath import ( + RANGE_XPATH, + AVL_AEROMAP_UID_XPATH, + AVL_PLOT_XPATH, + AVL_VORTEX_DISTR_XPATH, + AVL_FUSELAGE_XPATH, +) +from cpacspy.cpacsfunctions import get_value_or_default +from ceasiompy.utils.moduleinterfaces import get_module_path +from cpacspy.cpacspy import CPACS + +log = get_logger() + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= +def write_command_file( + avl_path, + case_dir_path, + alpha, + beta, + mach_number, + ref_velocity, + ref_density, + g_acceleration, + save_plots, +): + """Function to write the command file for AVL. + + Function 'write_command_file' writes the command file to + execute for AVL calculations. + + Args: + avl_path (Path) : path to the AVL input file + case_dir_path (Path) : path to the run case directory + alpha (float) : angle of attack [deg] + beta (float) : angle of attack [deg] + mach_number (float) : Mach number + ref_velocity (float) : reference upstream velocity [m/s] + ref_density (float) : reference upstream density [kg/m^3] + g_acceleration (float) : gravitational acceleration [m/s^2] + + Returns: + avl_commands.txt : write the command AVL file. + command_path (Path) : path to the command file. + """ + + command_path = str(case_dir_path) + "/avl_commands.txt" + pyavl_dir = get_module_path("PyAVL") + mass_path = Path(pyavl_dir, "files", "template.mass") + + if save_plots: + with open(command_path, "w") as command_file: + command_file.writelines( + [ + "load " + str(avl_path) + "\n", + "mass " + str(mass_path) + "\n", + "oper\n", + "g\n", + "h\n\n", + "a a " + str(alpha) + "\n", + "b b " + str(beta) + "\n", + "m\n", + "mn " + str(mach_number) + "\n", + "g " + str(g_acceleration) + "\n", + "d " + str(ref_density) + "\n", + "v " + str(ref_velocity) + "\n\n", + ] + ) + command_file.write("x\n") + command_file.writelines(["t\n", "h\n\n"]) + command_file.writelines(["g\n", "lo\n", "h\n\n"]) + command_file.write("x\n") + for force_file in ["ft", "fn", "fs", "fe", "st"]: + command_file.write(force_file + "\n") + command_file.write(force_file + ".txt\n") + command_file.write("\n\n\n") + command_file.write("quit") + + else: # same without lines saving figures + with open(command_path, "w") as command_file: + command_file.writelines( + [ + "load " + str(avl_path) + "\n", + "mass " + str(mass_path) + "\n", + "oper\n", + "a a " + str(alpha) + "\n", + "b b " + str(beta) + "\n", + "m\n", + "mn " + str(mach_number) + "\n", + "g " + str(g_acceleration) + "\n", + "d " + str(ref_density) + "\n", + "v " + str(ref_velocity) + "\n\n", + ] + ) + command_file.write("x\n") + for force_file in ["ft", "fn", "fs", "fe", "st"]: + command_file.write(force_file + "\n") + command_file.write(force_file + ".txt\n") + command_file.write("\n\n\n") + command_file.write("quit") + + # Print the command file for debugging + # with open(command_path, "r") as command_file: + # for line in command_file: + # print(line) + + return Path(command_path) + + +def get_aeromap_conditions(cpacs_path): + """Function read the flight conditions from the aeromap. + + Function 'get_aeromap_conditions' reads the flight conditions + (angle of attack, mach number...) from the aeromap of CEASIOMpy. + + Args: + cpacs_path (Path) : path to the cpacs input file + + Returns: + alt_list (list) : altitude of the cases. + mach_list (list) : mach number of the cases. + aoa_list (list) : angle of attack of the cases. + aos_list (list) : angle of sweep of the cases. + """ + cpacs = CPACS(cpacs_path) + + # Get the first aeroMap as default one or create automatically one + aeromap_list = cpacs.get_aeromap_uid_list() + + if aeromap_list: + aeromap_default = aeromap_list[0] + log.info(f"The aeromap is {aeromap_default}") + + aeromap_uid = get_value_or_default(cpacs.tixi, AVL_AEROMAP_UID_XPATH, aeromap_default) + + activate_aeromap = cpacs.get_aeromap_by_uid(aeromap_uid) + alt_list = activate_aeromap.get("altitude").tolist() + mach_list = activate_aeromap.get("machNumber").tolist() + aoa_list = activate_aeromap.get("angleOfAttack").tolist() + aos_list = activate_aeromap.get("angleOfSideslip").tolist() + + else: + default_aeromap = cpacs.create_aeromap("DefaultAeromap") + default_aeromap.description = "AeroMap created automatically" + + mach = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseMach", 0.3) + alt = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseAltitude", 10000) + + default_aeromap.add_row(alt=alt, mach=mach, aos=0.0, aoa=0.0) + default_aeromap.save() + + alt_list = [alt] + mach_list = [mach] + aoa_list = [0.0] + aos_list = [0.0] + + aeromap_uid = get_value_or_default(cpacs.tixi, AVL_AEROMAP_UID_XPATH, "DefaultAeromap") + log.info(f"{aeromap_uid} has been created") + + cpacs.save_cpacs(cpacs_path, overwrite=True) + return alt_list, mach_list, aoa_list, aos_list + + +def get_option_settings(cpacs_path): + """Function read the setting of the graphical user interface. + + Function 'get_option_settings' reads the setting to use in AVL + from the graphical user interface of CEASIOMpy. + + Args: + cpacs_path (Path) : path to the cpacs input file + + Returns: + save_plots (bool) : to save the geometry and results figures. + vortex_distribution (float) : distribution of the vortices. + Nchordwise (int) : number of chordwise vortices. + Nspanwise (int) : number of spanwise vortices. + """ + cpacs = CPACS(cpacs_path) + + save_plots = get_value_or_default(cpacs.tixi, AVL_PLOT_XPATH, False) + vortex_distribution_gui = get_value_or_default( + cpacs.tixi, AVL_VORTEX_DISTR_XPATH + "/Distribution", "equal" + ) + if vortex_distribution_gui == "cosine": + vortex_distribution = 1.0 + elif vortex_distribution_gui == "sine": + vortex_distribution = 2.0 + else: + vortex_distribution = 3.0 + Nchordwise = get_value_or_default(cpacs.tixi, AVL_VORTEX_DISTR_XPATH + "/Nchordwise", 5) + Nspanwise = get_value_or_default(cpacs.tixi, AVL_VORTEX_DISTR_XPATH + "/Nspanwise", 20) + integrate_fuselage = get_value_or_default(cpacs.tixi, AVL_FUSELAGE_XPATH, False) + + return save_plots, vortex_distribution, Nchordwise, Nspanwise, integrate_fuselage + + +# ================================================================================================= +# MAIN +# ================================================================================================= + +if __name__ == "__main__": + log.info("Nothing to execute!") diff --git a/ceasiompy/PyAVL/func/avlresults.py b/ceasiompy/PyAVL/func/avlresults.py new file mode 100644 index 000000000..031245153 --- /dev/null +++ b/ceasiompy/PyAVL/func/avlresults.py @@ -0,0 +1,207 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Extract results from AVL calculations and save them in a CPACS file. + +Python version: >=3.8 + +| Author: Romain Gauthier +| Creation: 2024-03-18 + +TODO: + + * + +""" + +# ================================================================================================= +# IMPORTS +# ================================================================================================= + +from pathlib import Path +import pandas as pd +import matplotlib.pyplot as plt + +from ceasiompy.utils.ceasiomlogger import get_logger +from ceasiompy.utils.commonxpath import AVL_AEROMAP_UID_XPATH + +from cpacspy.cpacsfunctions import get_value +from cpacspy.cpacspy import CPACS + +log = get_logger() + + +# ================================================================================================= +# CLASSES +# ================================================================================================= + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +def plot_lift_distribution(force_file_fs, aoa, aos, mach, alt, wkdir): + """Plot the lift distribution from AVL strip forces file (fs.txt) + + Args: + force_file_fs (Path): Path to the AVL strip forces file + aoa (float): angle of attack [deg] + aos (float): angle of sideslip [deg] + mach (float): mach number + alt (float): flight altitude [m] + wkir (path): path to save the plot + + Returns: + """ + y_list = [] + chord_list = [] + cl_list = [] + clnorm_list = [] + + with open(force_file_fs, "r") as fs: + for line in fs: + if "Cref =" in line: + cref = float(line.split()[5]) + + elif "# Spanwise =" in line: + number_strips = int(line.split()[7]) + + elif "Xle" in line: + number_data = 0 + for line in fs: + data = line.split() + y_list.append(float(data[2])) + chord_list.append(float(data[4])) + cl_list.append(float(data[9])) + clnorm_list.append(float(data[8])) + number_data += 1 + + # break when every line has been extracted + if number_data == number_strips: + break + + data_df = pd.DataFrame( + {"y": y_list, "chord": chord_list, "cl": cl_list, "cl_norm": clnorm_list} + ) + + data_df.sort_values(by="y", inplace=True) + data_df.reset_index(drop=True, inplace=True) + data_df["cl_cref"] = data_df["cl"] * data_df["chord"] / cref + + _, ax = plt.subplots(figsize=(10, 5)) + data_df.plot("y", "cl_norm", ax=ax, label="$c_{l\perp}$", linestyle="dashed", color="r") + data_df.plot("y", "cl", label="$c_l$", ax=ax, linestyle="dashed", color="#FFA500") + data_df.plot( + "y", "cl_cref", ax=ax, label="$c_l \cdot C/C_{ref}$", linestyle="solid", color="#41EE33" + ) + + plt.title( + ( + "Lift distribution along the wing span " + "($\\alpha=%.1f^{\circ}$, $\\beta=%.1f^{\circ}$, " + "$M=%.1f$, alt = %d m)" + ) + % (aoa, aos, mach, alt), + fontsize=14, + ) + + plt.ylabel("$C_l$", rotation=0, fontsize=12) + plt.legend(fontsize=12) + plt.grid() + plt.savefig(Path(wkdir, "lift_distribution.png")) + + +def get_avl_aerocoefs(force_file_ft): + """Get aerodynamic coefficients and velocity from AVL total forces file (ft.txt) + + Args: + force_file_ft (Path): Path to the AVL total forces file + + Returns: + cl, cd, cs, cmd, cms, cml: Aerodynamic coefficients + """ + + if not force_file_ft.is_file(): + raise FileNotFoundError(f"The AVL forces file '{force_file_ft}' has not been found!") + + cl, cd = None, None + + with open(force_file_ft) as f: + for line in f.readlines(): + if "CLtot" in line: + cl = float(line.split("=")[1].strip()) + if "CDtot" in line: + cd = float(line.split("=")[1].strip()) + if "Cmtot" in line: + cm = float(line.split("=")[2].strip()) + + return cl, cd, cm + + +def get_avl_results(cpacs_path, cpacs_out_path, wkdir): + """Function to write AVL results in a CPACS file. + + Function 'get_avl_results' gets available results from the latest AVL calculation and put them + at the correct place in the CPACS file. + + '/cpacs/vehicles/aircraft/model/analyses/aeroPerformance/aeroMap[n]/aeroPerformanceMap' + + Args: + cpacs_path (Path): Path to input CPACS file + cpacs_out_path (Path): Path to output CPACS file + wkdir (Path): Path to the working directory + + """ + + cpacs = CPACS(cpacs_path) + if not wkdir.exists(): + raise OSError(f"The working directory : {wkdir} does not exit!") + aeromap_uid = get_value(cpacs.tixi, AVL_AEROMAP_UID_XPATH) + + log.info(f"The aeromap uid is: {aeromap_uid}") + aeromap = cpacs.get_aeromap_by_uid(aeromap_uid) + + alt_list = aeromap.get("altitude").tolist() + mach_list = aeromap.get("machNumber").tolist() + aoa_list = aeromap.get("angleOfAttack").tolist() + aos_list = aeromap.get("angleOfSideslip").tolist() + + case_dir_list = [case_dir for case_dir in wkdir.iterdir() if "Case" in case_dir.name] + + for config_dir in sorted(case_dir_list): + if not config_dir.is_dir(): + continue + + ft_file_path = Path(config_dir, "ft.txt") + + if not ft_file_path.exists(): + raise FileNotFoundError("No result total forces 'ft.txt' file have been found!") + + fs_file_path = Path(config_dir, "fs.txt") + if not fs_file_path.exists(): + raise FileNotFoundError("No result strip forces 'fs.txt' file have been found!") + + case_nb = int(config_dir.name.split("_")[0].split("Case")[1]) + + aoa = aoa_list[case_nb] + aos = aos_list[case_nb] + mach = mach_list[case_nb] + alt = alt_list[case_nb] + + cl, cd, cm = get_avl_aerocoefs(ft_file_path) + plot_lift_distribution(fs_file_path, aoa, aos, mach, alt, wkdir=config_dir) + + aeromap.add_coefficients(alt=alt, mach=mach, aos=aos, aoa=aoa, cd=cd, cl=cl, cms=cm) + aeromap.save() + cpacs.save_cpacs(cpacs_out_path, overwrite=True) + + +# ================================================================================================= +# MAIN +# ================================================================================================= + +if __name__ == "__main__": + log.info("Nothing to execute!") diff --git a/ceasiompy/PyAVL/func/cpacs2avl.py b/ceasiompy/PyAVL/func/cpacs2avl.py new file mode 100644 index 000000000..04135baeb --- /dev/null +++ b/ceasiompy/PyAVL/func/cpacs2avl.py @@ -0,0 +1,659 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Script to convert CPACS file geometry into AVL geometry + +Python version: >=3.8 + +| Author: Romain Gauthier +| Adapted from : Aidan Jungo script cpacs2sumo.py +| Creation: 2024-03-14 + +TODO: + + * Improve link between wings and fuselages parts + +""" + +# ============================================================================== +# IMPORTS +# ============================================================================== + +from ceasiompy.utils.ceasiompyutils import get_results_directory +import math +import numpy as np +from pathlib import Path +from scipy import interpolate + +from ceasiompy.CPACS2SUMO.func.getprofile import get_profile_coord + +from ceasiompy.utils.ceasiomlogger import get_logger +from ceasiompy.utils.commonxpath import WINGS_XPATH, FUSELAGES_XPATH, REF_XPATH + +from ceasiompy.utils.generalclasses import SimpleNamespace, Transformation +from ceasiompy.utils.mathfunctions import euler2fix +from cpacspy.cpacsfunctions import open_tixi + +from ceasiompy.PyAVL.func.rotation3D import rotate_3D_points +from ceasiompy.PyAVL.func.avlconfig import get_option_settings + +log = get_logger() + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +def convert_cpacs_to_avl(cpacs_path, wkdir): + """Function to convert a CPACS file geometry into an AVL file geometry. + + Function 'convert_cpacs_to_avl' opens an input CPACS file with TIXI handle + and converts every element (as much as possible) in the AVL (.avl) format. + The output sumo file is saved in ... + + Source: + * https://github.com/cfsengineering/CEASIOMpy/blob/main/ceasiompy/CPACS2SUMO/cpacs2sumo.py + + Args: + cpacs_path (Path) : path to the CPACS input file + + Returns: + aircraft.avl : write the input AVL file + avl_path (Path) : path to the AVL input file + """ + tixi = open_tixi(cpacs_path) + + # Get the aircraft name + name_aircraft = tixi.getTextElement("/cpacs/header/name") + + results_dir = get_results_directory("PyAVL") + results_path = str(results_dir) + avl_path = str(results_dir) + "/" + name_aircraft + ".avl" + + with open(avl_path, 'w') as avl_file: + avl_file.write(name_aircraft + "\n\n") + + # Get the flight conditions + FLIGHT_XPATH = "/cpacs/vehicles/aircraft/model/analyses/" + \ + "aeroPerformance/aeroMap[1]/aeroPerformanceMap" + mach = tixi.getDoubleElement(FLIGHT_XPATH + '/machNumber') + AoA = 0 # tixi.getDoubleElement(FLIGHT_XPATH + '/angleOfAttack') + with open(avl_path, 'a') as avl_file: + # Mach number + avl_file.write('#Mach\n') + avl_file.write(str(mach) + "\n\n") + # Symmetry + avl_file.write("#IYsym IZsym Zsym\n") + avl_file.write("0\t0\t0\n\n") + + _, vortex_distribution, Nchordwise, Nspanwise, integrate_fuselage = get_option_settings( + cpacs_path) + + # Get the reference dimensions + area_ref = tixi.getDoubleElement(REF_XPATH + '/area') + chord_ref = tixi.getDoubleElement(REF_XPATH + '/length') + span_ref = area_ref / chord_ref + points_ref = np.array([tixi.getDoubleElement(REF_XPATH + '/point/x'), + tixi.getDoubleElement(REF_XPATH + '/point/y'), + tixi.getDoubleElement(REF_XPATH + '/point/z')]) + with open(avl_path, 'a') as avl_file: + # Reference dimensions + avl_file.write("#Sref Cref Bref\n") + avl_file.write(f"{area_ref:.3f}\t{chord_ref:.3f}\t{span_ref:.3f}\n\n") + # Reference location for moments/rotations + avl_file.write("#Xref Yref Zref\n") + for i_points in range(3): + avl_file.write(f"{points_ref[i_points]:.3f}\t") + avl_file.write("\n\n") + + # Fuselage(s) --------------------------------------------------------------- + + if tixi.checkElement(FUSELAGES_XPATH): + fus_cnt = tixi.getNamedChildrenCount(FUSELAGES_XPATH, "fuselage") + log.info(str(fus_cnt) + " fuselage has been found.") + else: + fus_cnt = 0 + log.warning("No fuselage has been found in this CPACS file!") + + if integrate_fuselage: + for i_fus in reversed(range(fus_cnt)): + fus_xpath = FUSELAGES_XPATH + "/fuselage[" + str(i_fus + 1) + "]" + fus_uid = tixi.getTextAttribute(fus_xpath, "uID") + fus_transf = Transformation() + fus_transf.get_cpacs_transf(tixi, fus_xpath) + + body_transf = Transformation() + body_transf.translation = fus_transf.translation + + # Convert angles + body_transf.rotation = euler2fix(fus_transf.rotation) + + # Add body origin + body_ori_str = ( + str(body_transf.translation.x) + + "\t" + + str(body_transf.translation.y) + + "\t" + + str(body_transf.translation.z) + ) + + # Write fuselage settings + with open(avl_path, 'a') as avl_file: + avl_file.write("#--------------------------------------------------\n") + avl_file.write("BODY\n") + avl_file.write("Fuselage\n\n") + avl_file.write("!Nbody Bspace\n") + avl_file.write("100\t1.0\n\n") + + # Scaling + avl_file.write("SCALE\n") + avl_file.write(str(fus_transf.scaling.x) + + "\t" + + str(fus_transf.scaling.y) + + "\t" + + str(fus_transf.scaling.z) + + "\n\n") + + # Translation + avl_file.write("TRANSLATE\n") + avl_file.write(body_ori_str + "\n\n") + + # avl_file.write("NOWAKE\n\n") + + # Positionings + if tixi.checkElement(fus_xpath + "/positionings"): + pos_cnt = tixi.getNamedChildrenCount(fus_xpath + "/positionings", "positioning") + log.info(str(fus_cnt) + ' "Positioning" has been found : ') + + pos_x_list = [] + pos_y_list = [] + pos_z_list = [] + from_sec_list = [] + to_sec_list = [] + + for i_pos in range(pos_cnt): + pos_xpath = fus_xpath + "/positionings/positioning[" + str(i_pos + 1) + "]" + + length = tixi.getDoubleElement(pos_xpath + "/length") + sweep_deg = tixi.getDoubleElement(pos_xpath + "/sweepAngle") + sweep = math.radians(sweep_deg) + dihedral_deg = tixi.getDoubleElement(pos_xpath + "/dihedralAngle") + dihedral = math.radians(dihedral_deg) + + # Get the corresponding translation of each positioning + pos_x_list.append(length * math.sin(sweep)) + pos_y_list.append(length * math.cos(dihedral) * math.cos(sweep)) + pos_z_list.append(length * math.sin(dihedral) * math.cos(sweep)) + + # Get which section are connected by the positioning + if tixi.checkElement(pos_xpath + "/fromSectionUID"): + from_sec = tixi.getTextElement(pos_xpath + "/fromSectionUID") + else: + from_sec = "" + from_sec_list.append(from_sec) + + if tixi.checkElement(pos_xpath + "/toSectionUID"): + to_sec = tixi.getTextElement(pos_xpath + "/toSectionUID") + else: + to_sec = "" + to_sec_list.append(to_sec) + + # Re-loop though the positioning to re-order them + for j_pos in range(pos_cnt): + if from_sec_list[j_pos] == "": + prev_pos_x = 0 + prev_pos_y = 0 + prev_pos_z = 0 + + elif from_sec_list[j_pos] == to_sec_list[j_pos - 1]: + prev_pos_x = pos_x_list[j_pos - 1] + prev_pos_y = pos_y_list[j_pos - 1] + prev_pos_z = pos_z_list[j_pos - 1] + + else: + index_prev = to_sec_list.index(from_sec_list[j_pos]) + prev_pos_x = pos_x_list[index_prev] + prev_pos_y = pos_y_list[index_prev] + prev_pos_z = pos_z_list[index_prev] + + pos_x_list[j_pos] += prev_pos_x + pos_y_list[j_pos] += prev_pos_y + pos_z_list[j_pos] += prev_pos_z + + else: + log.warning('No "positionings" have been found!') + pos_cnt = 0 + + # Sections + sec_cnt = tixi.getNamedChildrenCount(fus_xpath + "/sections", "section") + log.info(" -" + str(sec_cnt) + " fuselage sections have been found") + x_fuselage = np.zeros(sec_cnt) + y_fuselage_top = np.zeros(sec_cnt) + y_fuselage_bottom = np.zeros(sec_cnt) + fus_radius_vec = np.zeros(sec_cnt) + body_width_vec = np.zeros(sec_cnt) + body_height_vec = np.zeros(sec_cnt) + + if pos_cnt == 0: + pos_x_list = [0.0] * sec_cnt + pos_y_list = [0.0] * sec_cnt + pos_z_list = [0.0] * sec_cnt + + for i_sec in range(sec_cnt): + sec_xpath = fus_xpath + "/sections/section[" + str(i_sec + 1) + "]" + sec_uid = tixi.getTextAttribute(sec_xpath, "uID") + + sec_transf = Transformation() + sec_transf.get_cpacs_transf(tixi, sec_xpath) + + if sec_transf.rotation.x or sec_transf.rotation.y or sec_transf.rotation.z: + log.warning( + f"Sections '{sec_uid}' is rotated, it is" + "not possible to take that into account in SUMO !" + ) + + # Elements + elem_cnt = tixi.getNamedChildrenCount(sec_xpath + "/elements", "element") + + if elem_cnt > 1: + log.warning( + "Sections " + + sec_uid + + " contains multiple \ + element, it could be an issue for the conversion \ + to SUMO!" + ) + + for i_elem in range(elem_cnt): + elem_xpath = sec_xpath + "/elements/element[" + str(i_elem + 1) + "]" + elem_uid = tixi.getTextAttribute(elem_xpath, "uID") + + elem_transf = Transformation() + elem_transf.get_cpacs_transf(tixi, elem_xpath) + + if elem_transf.rotation.x or elem_transf.rotation.y or elem_transf.rotation.z: + log.warning( + f"Element '{elem_uid}' is rotated, it is" + "not possible to take that into account in SUMO !" + ) + + # Fuselage profiles + prof_uid = tixi.getTextElement(elem_xpath + "/profileUID") + prof_vect_x, prof_vect_y, prof_vect_z = get_profile_coord(tixi, prof_uid) + + prof_size_y = (max(prof_vect_y) - min(prof_vect_y)) / 2 + prof_size_z = (max(prof_vect_z) - min(prof_vect_z)) / 2 + + prof_vect_y[:] = [y / prof_size_y for y in prof_vect_y] + prof_vect_z[:] = [z / prof_size_z for z in prof_vect_z] + + prof_min_y = min(prof_vect_y) + prof_min_z = min(prof_vect_z) + + prof_vect_y[:] = [y - 1 - prof_min_y for y in prof_vect_y] + prof_vect_z[:] = [z - 1 - prof_min_z for z in prof_vect_z] + + # Could be a problem if they are less positionings than sections + # TODO: solve that! + pos_y_list[i_sec] += ((1 + prof_min_y) * prof_size_y) * elem_transf.scaling.y + pos_z_list[i_sec] += ((1 + prof_min_z) * prof_size_z) * elem_transf.scaling.z + + # Compute coordinates of the center of section + body_frm_center_x = ( + elem_transf.translation.x + sec_transf.translation.x + pos_x_list[i_sec] + ) * fus_transf.scaling.x + + body_frm_center_z = ( + elem_transf.translation.z * sec_transf.scaling.z + + sec_transf.translation.z + + pos_z_list[i_sec] + ) * fus_transf.scaling.z + + # Compute height and width of the section + body_frm_height = ( + prof_size_z + * 2 + * elem_transf.scaling.z + * sec_transf.scaling.z + * fus_transf.scaling.z + ) + body_frm_width = ( + prof_size_y + * 2 + * elem_transf.scaling.y + * sec_transf.scaling.y + * fus_transf.scaling.y + ) + + # Compute diameter of the section as the mean between height and width + # AVL assumes only circular cross section for fuselage + fus_radius = np.mean([body_frm_height, body_frm_width]) / 2 + fus_radius_vec[i_sec] = (fus_radius) + + # Save the coordinates of the fuselage + x_fuselage[i_sec] = body_frm_center_x + y_fuselage_top[i_sec] = body_frm_center_z + fus_radius + y_fuselage_bottom[i_sec] = body_frm_center_z - fus_radius + + body_width_vec[i_sec] = body_frm_width + body_height_vec[i_sec] = body_frm_height + + fus_z_profile = interpolate.interp1d( + x_fuselage + body_transf.translation.x, y_fuselage_top - fus_radius_vec) + fus_radius_profile = interpolate.interp1d( + x_fuselage + body_transf.translation.x, fus_radius_vec) + + fus_dat_path = results_path + "/" + fus_uid + ".dat" + + with open(fus_dat_path, 'w') as fus_file: + fus_file.write("fuselage" + str(i_fus + 1) + "\n") + + # Write coordinates of the top surface + for x_fus, y_fus in reversed(list(zip(x_fuselage[1:], y_fuselage_top[1:]))): + # fus_file.write(str(x_fus) + "\t" + str(y_fus) + "\n") + fus_file.write(f"{x_fus:.3f}\t{y_fus:.3f}\n") + + # Write coordinates of the nose of the fuselage + y_nose = np.mean([y_fuselage_top[0], y_fuselage_bottom[0]]) + # fus_file.write(str(x_fuselage[0]) + "\t" + str(y_nose) + "\n") + fus_file.write(f"{x_fuselage[0]:.3f}\t{y_nose:.3f}\n") + + # Write coordinates of the bottom surface + for x_fus, y_fus in zip(x_fuselage[1:], y_fuselage_bottom[1:]): + # fus_file.write(str(x_fus) + "\t" + str(y_fus) + "\n") + fus_file.write(f"{x_fus:.3f}\t{y_fus:.3f}\n") + + with open(avl_path, 'a') as avl_file: + avl_file.write("BFILE\n") + avl_file.write(fus_dat_path + "\n\n") + + # Wing(s) ------------------------------------------------------------------ + if tixi.checkElement(WINGS_XPATH): + wing_cnt = tixi.getNamedChildrenCount(WINGS_XPATH, "wing") + log.info(str(wing_cnt) + " wings has been found.") + else: + wing_cnt = 0 + log.warning("No wings has been found in this CPACS file!") + + if vortex_distribution > 3 or vortex_distribution < -3: + log.warning( + "The vortex distribution is not in the range [-3 ; 3]. " + + "Default value of 1 will be used.") + vortex_distribution = 1 + + for i_wing in range(wing_cnt): + root_defined = False + wing_xpath = WINGS_XPATH + "/wing[" + str(i_wing + 1) + "]" + wing_transf = Transformation() + wing_transf.get_cpacs_transf(tixi, wing_xpath) + + # Create a class for the transformation of the WingSkeleton + wg_sk_transf = Transformation() + + # Convert WingSkeleton rotation + wg_sk_transf.rotation = euler2fix(wing_transf.rotation) + + # Add WingSkeleton origin + wg_sk_transf.translation = wing_transf.translation + wg_sk_ori_str = ( + str(round(wg_sk_transf.translation.x, 3)) + + "\t" + + str(round(wg_sk_transf.translation.y, 3)) + + "\t" + + str(round(wg_sk_transf.translation.z, 3)) + ) + + # Write wing settings + with open(avl_path, 'a') as avl_file: + avl_file.write("#--------------------------------------------------\n") + avl_file.write("SURFACE\n") + avl_file.write("Wing\n\n") + avl_file.write("!Nchordwise Cspace Nspanwise Sspace\n") + avl_file.write( + f"{Nchordwise} {vortex_distribution} {Nspanwise} {vortex_distribution}\n\n") + avl_file.write('COMPONENT\n') + avl_file.write("1\n\n") + + # Symmetry + if tixi.checkAttribute(wing_xpath, "symmetry"): + if tixi.getTextAttribute(wing_xpath, "symmetry") == "x-z-plane": + avl_file.write('YDUPLICATE\n') + avl_file.write("0\n\n") + + # Angle + avl_file.write('ANGLE\n') + avl_file.write(str(AoA) + "\n\n") + + # Scaling + avl_file.write("SCALE\n") + avl_file.write(str(wing_transf.scaling.x) + + "\t" + + str(wing_transf.scaling.y) + + "\t" + + str(wing_transf.scaling.z) + + "\n\n") + + # Translation + avl_file.write("TRANSLATE\n") + avl_file.write(wg_sk_ori_str + "\n\n") + + # Positionings + if tixi.checkElement(wing_xpath + "/positionings"): + pos_cnt = tixi.getNamedChildrenCount(wing_xpath + "/positionings", "positioning") + log.info(str(pos_cnt) + ' "positioning" has been found : ') + + pos_x_list = [] + pos_y_list = [] + pos_z_list = [] + from_sec_list = [] + to_sec_list = [] + + for i_pos in range(pos_cnt): + pos_xpath = wing_xpath + "/positionings/positioning[" + str(i_pos + 1) + "]" + + length = tixi.getDoubleElement(pos_xpath + "/length") + sweep_deg = tixi.getDoubleElement(pos_xpath + "/sweepAngle") + sweep = math.radians(sweep_deg) + dihedral_deg = tixi.getDoubleElement(pos_xpath + "/dihedralAngle") + dihedral = math.radians(dihedral_deg) + + # Get the corresponding translation of each positioning + pos_x_list.append(length * math.sin(sweep)) + pos_y_list.append(length * math.cos(dihedral) * math.cos(sweep)) + pos_z_list.append(length * math.sin(dihedral) * math.cos(sweep)) + + # Get which section are connected by the positioning + if tixi.checkElement(pos_xpath + "/fromSectionUID"): + from_sec = tixi.getTextElement(pos_xpath + "/fromSectionUID") + else: + from_sec = "" + from_sec_list.append(from_sec) + + if tixi.checkElement(pos_xpath + "/toSectionUID"): + to_sec = tixi.getTextElement(pos_xpath + "/toSectionUID") + else: + to_sec = "" + to_sec_list.append(to_sec) + + # Re-loop though the positioning to re-order them + for j_pos in range(pos_cnt): + if from_sec_list[j_pos] == "": + prev_pos_x = 0 + prev_pos_y = 0 + prev_pos_z = 0 + elif from_sec_list[j_pos] == to_sec_list[j_pos - 1]: + prev_pos_x = pos_x_list[j_pos - 1] + prev_pos_y = pos_y_list[j_pos - 1] + prev_pos_z = pos_z_list[j_pos - 1] + else: + index_prev = to_sec_list.index(from_sec_list[j_pos]) + prev_pos_x = pos_x_list[index_prev] + prev_pos_y = pos_y_list[index_prev] + prev_pos_z = pos_z_list[index_prev] + + pos_x_list[j_pos] += prev_pos_x + pos_y_list[j_pos] += prev_pos_y + pos_z_list[j_pos] += prev_pos_z + + else: + log.warning('No "positionings" have been found!') + pos_cnt = 0 + + # Sections + sec_cnt = tixi.getNamedChildrenCount(wing_xpath + "/sections", "section") + log.info(" -" + str(sec_cnt) + " wing sections have been found") + + if pos_cnt == 0: + pos_x_list = [0.0] * sec_cnt + pos_y_list = [0.0] * sec_cnt + pos_z_list = [0.0] * sec_cnt + + for i_sec in range(sec_cnt): + sec_xpath = wing_xpath + "/sections/section[" + str(i_sec + 1) + "]" + sec_uid = tixi.getTextAttribute(sec_xpath, "uID") + sec_transf = Transformation() + sec_transf.get_cpacs_transf(tixi, sec_xpath) + + # Elements + elem_cnt = tixi.getNamedChildrenCount(sec_xpath + "/elements", "element") + + if elem_cnt > 1: + log.warning( + f"Sections {sec_uid} contains multiple element," + " it could be an issue for the conversion to SUMO!" + ) + + for i_elem in range(elem_cnt): + elem_xpath = sec_xpath + "/elements/element[" + str(i_elem + 1) + "]" + elem_transf = Transformation() + elem_transf.get_cpacs_transf(tixi, elem_xpath) + + # Get wing profile (airfoil) + prof_uid = tixi.getTextElement(elem_xpath + "/airfoilUID") + prof_vect_x, prof_vect_y, prof_vect_z = get_profile_coord(tixi, prof_uid) + foil_dat_path = results_path + "/" + prof_uid + ".dat" + + with open(foil_dat_path, 'w') as dat_file: + dat_file.write(prof_uid + "\n") + # Limit the number of points to 100 (otherwise AVL error) + if len(prof_vect_x) < 100: + for coord_x, coord_z in zip(prof_vect_x, prof_vect_z): + dat_file.write(str(coord_x) + '\t' + str(coord_z) + "\n") + else: + step = round(len(prof_vect_x) / 100) + for coord_x, coord_z in zip(prof_vect_x[0:len(prof_vect_x):step], + prof_vect_z[0:len(prof_vect_x):step]): + dat_file.write(str(coord_x) + '\t' + str(coord_z) + "\n") + + # Apply scaling + for i, item in enumerate(prof_vect_x): + prof_vect_x[i] = ( + item * elem_transf.scaling.x * sec_transf.scaling.x * wing_transf.scaling.x + ) + for i, item in enumerate(prof_vect_y): + prof_vect_y[i] = ( + item * elem_transf.scaling.y * sec_transf.scaling.y * wing_transf.scaling.y + ) + for i, item in enumerate(prof_vect_z): + prof_vect_z[i] = ( + item * elem_transf.scaling.z * sec_transf.scaling.z * wing_transf.scaling.z + ) + + prof_size_x = max(prof_vect_x) - min(prof_vect_x) + prof_size_y = max(prof_vect_y) - min(prof_vect_y) + + if prof_size_y == 0: + prof_vect_x[:] = [x / prof_size_x for x in prof_vect_x] + prof_vect_z[:] = [z / prof_size_x for z in prof_vect_z] + # Is it correct to divide by prof_size_x ???? + + wg_sec_chord = prof_size_x + else: + log.error("An airfoil profile is not define correctly") + + # Add rotation from element and sections + # Adding the two angles: Maybe not work in every case!!! + add_rotation = SimpleNamespace() + add_rotation.x = elem_transf.rotation.x + \ + sec_transf.rotation.x + wg_sk_transf.rotation.x + add_rotation.y = elem_transf.rotation.y + \ + sec_transf.rotation.y + wg_sk_transf.rotation.y + add_rotation.z = elem_transf.rotation.z + \ + sec_transf.rotation.z + wg_sk_transf.rotation.z + + # Get Section rotation + wg_sec_rot = euler2fix(add_rotation) + wg_sec_dihed = math.radians(wg_sec_rot.x) + wg_sec_twist = math.radians(wg_sec_rot.y) + wg_sec_yaw = math.radians(wg_sec_rot.z) + + # Define the leading edge position from translations + x_LE = sec_transf.translation.x + elem_transf.translation.x + y_LE = sec_transf.translation.y + elem_transf.translation.y + z_LE = sec_transf.translation.z + elem_transf.translation.z + + if all(abs(value) < 1e-6 for value in pos_y_list): + x_LE_rot, y_LE_rot, z_LE_rot = rotate_3D_points( + x_LE, y_LE, z_LE, wg_sec_dihed, wg_sec_twist, wg_sec_yaw) + else: + x_LE_rot, y_LE_rot, z_LE_rot = rotate_3D_points( + pos_x_list[i_sec], pos_y_list[i_sec], pos_z_list[i_sec], + wg_sec_dihed, wg_sec_twist, wg_sec_yaw) + + # Compute the absolute location of the leading edge + x_LE_abs = x_LE_rot + wg_sk_transf.translation.x + y_LE_abs = y_LE_rot + wg_sk_transf.translation.y + z_LE_abs = z_LE_rot + wg_sk_transf.translation.z + + if integrate_fuselage: + # Compute the radius of the fuselage and the height difference ... + # between fuselage center and leading edge + radius_fus = fus_radius_profile(x_LE_abs + wg_sec_chord / 2) + fus_z_center = fus_z_profile(x_LE_abs + wg_sec_chord / 2) + delta_z = np.abs(fus_z_center + body_transf.translation.z - z_LE_abs) + + # If the root wing section is inside the fuselage, translate it to... + # the fuselage border + # To make sure there is no wing part inside the fuselage + if integrate_fuselage and np.sqrt((y_LE_abs)**2 + (delta_z)**2) < radius_fus and \ + wg_sec_dihed < math.pi / 2 and root_defined is False: + + y_LE_abs += np.sqrt(radius_fus**2 - delta_z**2) - y_LE_abs + y_LE_rot = y_LE_abs - wg_sk_transf.translation.y + root_defined = True + with open(avl_path, 'a') as avl_file: + avl_file.write("#---------------\n") + avl_file.write("SECTION\n") + avl_file.write("#Xle Yle Zle Chord Ainc\n") + avl_file.write(f"{x_LE_rot:.3f} {y_LE_rot:.3f} {z_LE_rot:.3f} " + f"{(wg_sec_chord):.3f} {wg_sec_rot.y}\n\n") + + avl_file.write("AFILE\n") + avl_file.write(foil_dat_path + "\n\n") + + elif integrate_fuselage is False or \ + np.sqrt((y_LE_abs)**2 + (delta_z)**2) > radius_fus \ + or wg_sec_dihed > 0.95 * math.pi / 2: + + # Write the leading edge coordinates and the airfoil file + with open(avl_path, 'a') as avl_file: + avl_file.write("#---------------\n") + avl_file.write("SECTION\n") + avl_file.write("#Xle Yle Zle Chord Ainc\n") + avl_file.write(f"{x_LE_rot:.3f} {y_LE_rot:.3f} {z_LE_rot:.3f} " + f"{(wg_sec_chord):.3f} {wg_sec_rot.y}\n\n") + avl_file.write("AFILE\n") + avl_file.write(foil_dat_path + "\n\n") + + return Path(avl_path) + + +# ================================================================================================= +# MAIN +# ================================================================================================= + +if __name__ == "__main__": + + log.info("Nothing to execute!") diff --git a/ceasiompy/PyAVL/func/rotation3D.py b/ceasiompy/PyAVL/func/rotation3D.py new file mode 100644 index 000000000..9b4c3deb0 --- /dev/null +++ b/ceasiompy/PyAVL/func/rotation3D.py @@ -0,0 +1,88 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Function to apply a 3D rotation to the coordinates of a point. + +Python version: >=3.8 + +| Author: Romain Gauthier +| Creation: 2024-03-13 + +""" + + +# ============================================================================== +# IMPORTS +# ============================================================================== + +from ceasiompy.utils.ceasiomlogger import get_logger +import numpy as np +import math + +log = get_logger() + + +# ============================================================================== +# FUNCTIONS +# ============================================================================== + + +def rotate_3D_points(x, y, z, angle_x, angle_y, angle_z): + """Function to apply a 3D rotation to the coordinates of a point + + Function 'rotate_3D_points' returns the rotated points after applying + a 3D rotation matrix. + + Source: + * https://en.wikipedia.org/wiki/Rotation_matrix + + Args: + x (float): x coordinate of the initial point + y (float): y coordinate of the initial point + z (float): z coordinate of the initial point + angle_x (float): rotation angle around x-axis [rad] + angle_y (float): rotation angle around y-axis [rad] + angle_z (float): rotation angle around z-axis [rad] + + Returns: + x_rot (float): x coordinate of the rotated point + y_rot (float): y coordinate of the rotated point + z_rot (float): z coordinate of the rotated point + """ + R11 = math.cos(angle_z) * math.cos(angle_y) + R12 = math.cos(angle_z) * math.sin(angle_y) * math.sin(angle_x) - \ + math.sin(angle_z) * math.cos(angle_x) + R13 = math.cos(angle_z) * math.sin(angle_y) * math.cos(angle_x) + \ + math.sin(angle_z) * math.sin(angle_x) + R21 = math.sin(angle_z) * math.cos(angle_y) + R22 = math.sin(angle_z) * math.sin(angle_y) * math.sin(angle_x) + \ + math.cos(angle_z) * math.cos(angle_x) + R23 = math.sin(angle_z) * math.sin(angle_y) * math.cos(angle_x) - \ + math.cos(angle_z) * math.sin(angle_x) + R31 = -math.sin(angle_y) + R32 = math.cos(angle_y) * math.sin(angle_x) + R33 = math.cos(angle_y) * math.cos(angle_x) + + rotation_matrix = np.array([[R11, R12, R13], + [R21, R22, R23], + [R31, R32, R33]]) + + x_rot = x * rotation_matrix[0, 0] + y * \ + rotation_matrix[0, 1] + z * rotation_matrix[0, 2] + y_rot = x * rotation_matrix[1, 0] + y * \ + rotation_matrix[1, 1] + z * rotation_matrix[1, 2] + z_rot = x * rotation_matrix[2, 0] + y * \ + rotation_matrix[2, 1] + z * rotation_matrix[2, 2] + + return x_rot, y_rot, z_rot + + +# ============================================================================== +# MAIN +# ============================================================================== + +if __name__ == "__main__": + + print("Nothing to execute!") diff --git a/ceasiompy/PyAVL/tests/avl_command_template.txt b/ceasiompy/PyAVL/tests/avl_command_template.txt new file mode 100644 index 000000000..92a49a2d9 --- /dev/null +++ b/ceasiompy/PyAVL/tests/avl_command_template.txt @@ -0,0 +1,37 @@ +load /path/to/avl/input/file/aircraft.avl +mass /users/disk8/cfse3/Stage_Romain/CEASIOMpy/ceasiompy/PyAVL/files/template.mass +oper +g +h + +a a 5.0 +b b 0.0 +m +mn 0.3 +g 9.803565306802405 +d 1.1116596736996904 +v 100.93037463067732 + +x +t +h + +g +lo +h + +x +ft +ft.txt +fn +fn.txt +fs +fs.txt +fe +fe.txt +st +st.txt + + + +quit \ No newline at end of file diff --git a/ceasiompy/PyAVL/tests/fs_template.txt b/ceasiompy/PyAVL/tests/fs_template.txt new file mode 100644 index 000000000..25bc3c4ec --- /dev/null +++ b/ceasiompy/PyAVL/tests/fs_template.txt @@ -0,0 +1,80 @@ + --------------------------------------------------------------- + Surface and Strip Forces by surface + + Sref = 0.27000E-01 Cref = 0.70000E-01 Bref = 0.39200 + Xref = 0.19200 Yref = 0.0000 Zref = 0.0000 + + Surface # 1 Wing + # Chordwise = 5 # Spanwise = 20 First strip = 1 + Surface area Ssurf = 0.013703 Ave. chord Cave = 0.067500 + + Forces referred to Sref, Cref, Bref about Xref, Yref, Zref + Standard axis orientation, X fwd, Z down + CLsurf = 0.17532 Clsurf = -0.04113 + CYsurf = 0.00714 Cmsurf = -0.00681 + CDsurf = 0.00312 Cnsurf = -0.00444 + CDisurf = 0.00312 CDvsurf = 0.00000 + + Forces referred to Ssurf, Cave + CLsurf = 0.34545 CDsurf = 0.00614 + + Strip Forces referred to Strip Area, Chord + j Xle Yle Zle Chord Area c_cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c + 1 0.1061 0.0051 0.0000 0.0889 0.0009 0.0260 0.0168 0.4585 0.2926 0.0173 0.0000 -0.0171 -0.0701 0.308 + 2 0.1144 0.0152 0.0000 0.0866 0.0009 0.0263 0.0246 0.4763 0.3040 0.0134 0.0000 -0.0112 -0.0677 0.287 + 3 0.1226 0.0254 0.0000 0.0844 0.0009 0.0266 0.0282 0.4935 0.3150 0.0113 0.0000 -0.0074 -0.0668 0.274 + 4 0.1309 0.0355 0.0000 0.0821 0.0008 0.0267 0.0303 0.5097 0.3253 0.0098 0.0000 -0.0050 -0.0669 0.265 + 5 0.1391 0.0457 0.0000 0.0799 0.0008 0.0267 0.0315 0.5247 0.3349 0.0085 0.0000 -0.0035 -0.0676 0.260 + 6 0.1474 0.0558 0.0000 0.0776 0.0008 0.0266 0.0323 0.5386 0.3438 0.0076 0.0000 -0.0024 -0.0684 0.257 + 7 0.1556 0.0660 0.0000 0.0754 0.0008 0.0265 0.0328 0.5514 0.3520 0.0067 0.0000 -0.0017 -0.0694 0.255 + 8 0.1639 0.0761 0.0000 0.0731 0.0007 0.0262 0.0332 0.5632 0.3595 0.0060 0.0000 -0.0011 -0.0704 0.253 + 9 0.1721 0.0863 0.0000 0.0709 0.0007 0.0259 0.0336 0.5740 0.3663 0.0054 0.0000 -0.0007 -0.0714 0.252 + 10 0.1804 0.0964 0.0000 0.0686 0.0007 0.0255 0.0341 0.5836 0.3725 0.0048 0.0000 -0.0003 -0.0723 0.251 + 11 0.1886 0.1066 0.0000 0.0664 0.0007 0.0250 0.0349 0.5920 0.3778 0.0042 0.0000 0.0001 -0.0730 0.250 + 12 0.1969 0.1167 0.0000 0.0641 0.0007 0.0244 0.0359 0.5990 0.3823 0.0037 0.0000 0.0006 -0.0735 0.248 + 13 0.2051 0.1269 0.0000 0.0619 0.0006 0.0238 0.0374 0.6041 0.3856 0.0032 0.0000 0.0011 -0.0737 0.247 + 14 0.2134 0.1370 0.0000 0.0596 0.0006 0.0230 0.0395 0.6068 0.3873 0.0026 0.0000 0.0019 -0.0734 0.245 + 15 0.2216 0.1472 0.0000 0.0574 0.0006 0.0221 0.0425 0.6058 0.3866 0.0021 0.0000 0.0030 -0.0724 0.242 + 16 0.2299 0.1573 0.0000 0.0551 0.0006 0.0210 0.0465 0.5991 0.3824 0.0015 0.0000 0.0046 -0.0703 0.238 + 17 0.2381 0.1675 0.0000 0.0529 0.0005 0.0196 0.0519 0.5831 0.3721 0.0008 0.0000 0.0071 -0.0664 0.231 + 18 0.2464 0.1776 0.0000 0.0506 0.0005 0.0177 0.0586 0.5506 0.3514 -0.0001 0.0000 0.0110 -0.0594 0.219 + 19 0.2546 0.1878 0.0000 0.0484 0.0005 0.0150 0.0659 0.4877 0.3113 -0.0013 0.0000 0.0162 -0.0475 0.198 + 20 0.2629 0.1979 0.0000 0.0461 0.0005 0.0106 0.0727 0.3610 0.2304 -0.0027 0.0000 0.0203 -0.0288 0.162 + + Surface # 2 Wing (YDUP) + # Chordwise = 5 # Spanwise = 20 First strip = 21 + Surface area Ssurf = 0.013703 Ave. chord Cave = 0.067500 + + Forces referred to Sref, Cref, Bref about Xref, Yref, Zref + Standard axis orientation, X fwd, Z down + CLsurf = 0.17532 Clsurf = 0.04113 + CYsurf = -0.00714 Cmsurf = -0.00681 + CDsurf = 0.00312 Cnsurf = 0.00444 + CDisurf = 0.00312 CDvsurf = 0.00000 + + Forces referred to Ssurf, Cave + CLsurf = 0.34545 CDsurf = 0.00614 + + Strip Forces referred to Strip Area, Chord + j Xle Yle Zle Chord Area c_cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c + 21 0.1061 -0.0051 0.0000 0.0889 0.0009 0.0260 0.0168 0.4585 0.2926 0.0173 0.0000 -0.0171 0.0701 0.308 + 22 0.1144 -0.0152 0.0000 0.0866 0.0009 0.0263 0.0246 0.4763 0.3040 0.0134 0.0000 -0.0112 0.0677 0.287 + 23 0.1226 -0.0254 0.0000 0.0844 0.0009 0.0266 0.0282 0.4935 0.3150 0.0113 0.0000 -0.0074 0.0668 0.274 + 24 0.1309 -0.0355 0.0000 0.0821 0.0008 0.0267 0.0303 0.5097 0.3253 0.0098 0.0000 -0.0050 0.0669 0.265 + 25 0.1391 -0.0457 0.0000 0.0799 0.0008 0.0267 0.0315 0.5247 0.3349 0.0085 0.0000 -0.0035 0.0676 0.260 + 26 0.1474 -0.0558 0.0000 0.0776 0.0008 0.0266 0.0323 0.5386 0.3438 0.0076 0.0000 -0.0024 0.0684 0.257 + 27 0.1556 -0.0660 0.0000 0.0754 0.0008 0.0265 0.0328 0.5514 0.3520 0.0067 0.0000 -0.0017 0.0694 0.255 + 28 0.1639 -0.0761 0.0000 0.0731 0.0007 0.0262 0.0332 0.5632 0.3595 0.0060 0.0000 -0.0011 0.0704 0.253 + 29 0.1721 -0.0863 0.0000 0.0709 0.0007 0.0259 0.0336 0.5740 0.3663 0.0054 0.0000 -0.0007 0.0714 0.252 + 30 0.1804 -0.0964 0.0000 0.0686 0.0007 0.0255 0.0341 0.5836 0.3725 0.0048 0.0000 -0.0003 0.0723 0.251 + 31 0.1886 -0.1066 0.0000 0.0664 0.0007 0.0250 0.0349 0.5920 0.3778 0.0042 0.0000 0.0001 0.0730 0.250 + 32 0.1969 -0.1167 0.0000 0.0641 0.0007 0.0244 0.0359 0.5990 0.3823 0.0037 0.0000 0.0006 0.0735 0.248 + 33 0.2051 -0.1269 0.0000 0.0619 0.0006 0.0238 0.0374 0.6041 0.3856 0.0032 0.0000 0.0011 0.0737 0.247 + 34 0.2134 -0.1370 0.0000 0.0596 0.0006 0.0230 0.0395 0.6068 0.3873 0.0026 0.0000 0.0019 0.0734 0.245 + 35 0.2216 -0.1472 0.0000 0.0574 0.0006 0.0221 0.0425 0.6058 0.3866 0.0021 0.0000 0.0030 0.0724 0.242 + 36 0.2299 -0.1573 0.0000 0.0551 0.0006 0.0210 0.0465 0.5991 0.3824 0.0015 0.0000 0.0046 0.0703 0.238 + 37 0.2381 -0.1675 0.0000 0.0529 0.0005 0.0196 0.0519 0.5831 0.3721 0.0008 0.0000 0.0071 0.0664 0.231 + 38 0.2464 -0.1776 0.0000 0.0506 0.0005 0.0177 0.0586 0.5506 0.3514 -0.0001 0.0000 0.0110 0.0594 0.219 + 39 0.2546 -0.1878 0.0000 0.0484 0.0005 0.0150 0.0659 0.4877 0.3113 -0.0013 0.0000 0.0162 0.0475 0.198 + 40 0.2629 -0.1979 0.0000 0.0461 0.0005 0.0106 0.0727 0.3610 0.2304 -0.0027 0.0000 0.0203 0.0288 0.162 + --------------------------------------------------------------- \ No newline at end of file diff --git a/ceasiompy/PyAVL/tests/ft_template.txt b/ceasiompy/PyAVL/tests/ft_template.txt new file mode 100644 index 000000000..1b2939b90 --- /dev/null +++ b/ceasiompy/PyAVL/tests/ft_template.txt @@ -0,0 +1,31 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: labARscaled + # Surfaces = 2 + # Strips = 40 + # Vortices = 200 + + Sref = 0.27000E-01 Cref = 0.70000E-01 Bref = 0.39200 + Xref = 0.19200 Yref = 0.0000 Zref = 0.0000 + + Standard axis orientation, X fwd, Z down + + Run case: -unnamed- + + Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Beta = 0.00000 qc/2V = 0.00000 + Mach = 0.300 rb/2V = -0.00000 r'b/2V = -0.00000 + + CXtot = 0.02435 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.01362 + CZtot = -0.34984 Cntot = -0.00000 Cn'tot = 0.00000 + + CLtot = 0.35063 + CDtot = 0.00624 + CDvis = 0.00000 CDind = 0.0062360 + CLff = 0.35118 CDff = 0.0064539 | Trefftz + CYff = 0.00000 e = 1.0688 | Plane + + + --------------------------------------------------------------- \ No newline at end of file diff --git a/ceasiompy/PyAVL/tests/test_avlconfig.py b/ceasiompy/PyAVL/tests/test_avlconfig.py new file mode 100644 index 000000000..acf31e749 --- /dev/null +++ b/ceasiompy/PyAVL/tests/test_avlconfig.py @@ -0,0 +1,105 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Test functions of 'ceasiompy/PyAVL/func/avlconfig.py' + +Python version: >=3.8 + +| Author : Romain Gauthier +| Creation: 2024-06-06 + +""" + +# ================================================================================================= +# IMPORTS +# ================================================================================================= + +from pathlib import Path + +from ceasiompy.PyAVL.func.avlconfig import ( + get_aeromap_conditions, + get_option_settings, + write_command_file, +) +from ceasiompy.utils.commonpaths import CPACS_FILES_PATH + +CPACS_IN_PATH = Path(CPACS_FILES_PATH, "labARscaled.xml") + +MODULE_DIR = Path(__file__).parent +CASE_DIR = Path(MODULE_DIR, "AVLpytest") +COMMAND_TEM_DIR = Path(MODULE_DIR, "avl_command_template.txt") + +# ================================================================================================= +# CLASSES +# ================================================================================================= + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +def test_write_command_file(tmp_path): + test_path = Path("/path", "to", "avl", "input", "file", "aircraft.avl") + + write_command_file( + avl_path=test_path, + case_dir_path=tmp_path, + alpha=5.0, + beta=0.0, + mach_number=0.3, + ref_velocity=100.93037463067732, + ref_density=1.1116596736996904, + g_acceleration=9.803565306802405, + save_plots=True, + ) + + file_exists = Path(tmp_path, "avl_commands.txt").exists() + assert file_exists, "File 'avl_commands.txt' not found." + + if file_exists: + COMMAND_DIR = Path(tmp_path, "avl_commands.txt") + with open(COMMAND_TEM_DIR, "r") as file1, open(COMMAND_DIR, "r") as file2: + for line1, line2 in zip(file1, file2): + if "mass" not in line1: + assert line1 == line2, "File 'avl_commands.txt' not correct." + + # Check for any remaining lines in either file + assert not file1.read() or not file2.read(), "File 'avl_commands.txt' not correct." + + +def test_get_aeromap_conditions(): + alt_list, mach_list, aoa_list, aos_list = get_aeromap_conditions(CPACS_IN_PATH) + assert alt_list[0] == 1000.0, "Altitude from aeromap not correct, should be 1000.0 meters." + assert mach_list[0] == 0.3, "Mach number from aeromap not correct, should be 0.3." + assert aoa_list[0] == 5.0, "Aoa from aeromap not correct, should be 5.0 degrees." + assert aos_list[0] == 0.0, "Altitude from aeromap not correct, should be 0.0 degrees" + + +def test_get_option_settings(): + ( + save_plots, + vortex_distribution, + Nchordwise, + Nspanwise, + integrate_fuselage, + ) = get_option_settings(CPACS_IN_PATH) + + assert not save_plots, "Option 'save_plots' should be 'False'." + assert vortex_distribution == 3.0, "Option 'vortex_distribution' should be '3.0'." + assert Nchordwise == 5, "Option 'Nchordwise' should be '5'." + assert Nspanwise == 20, "Option 'Nspanwise' should be '20'." + assert not integrate_fuselage, "Option 'integrate_fuselage' should be 'False'." + + +# ================================================================================================= +# MAIN +# ================================================================================================= + + +if __name__ == "__main__": + print("Test avlconfig.py") + print("To run test use the following command:") + print(">> pytest -v") diff --git a/ceasiompy/PyAVL/tests/test_avlresults.py b/ceasiompy/PyAVL/tests/test_avlresults.py new file mode 100644 index 000000000..4b1909b80 --- /dev/null +++ b/ceasiompy/PyAVL/tests/test_avlresults.py @@ -0,0 +1,69 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Test functions of 'ceasiompy/PyAVL/func/avlresults.py' + +Python version: >=3.8 + +| Author : Romain Gauthier +| Creation: 2024-06-07 + +""" + +# ================================================================================================= +# IMPORTS +# ================================================================================================= +from pathlib import Path +import pytest +from ceasiompy.PyAVL.func.avlresults import get_avl_aerocoefs, plot_lift_distribution + +from ceasiompy.utils.commonpaths import CPACS_FILES_PATH + +MODULE_DIR = Path(__file__).parent + +CPACS_IN_PATH = Path(CPACS_FILES_PATH, "labARscaled.xml") +FT_TEMPLATE = Path(MODULE_DIR, "ft_template.txt") + +# ================================================================================================= +# CLASSES +# ================================================================================================= + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +def test_plot_lift_distribution(tmp_path): + plot_lift_distribution( + force_file_fs=Path(MODULE_DIR, "fs_template.txt"), + aoa=5, + aos=0, + mach=0.3, + alt=1000, + wkdir=tmp_path, + ) + + assert Path( + tmp_path, "lift_distribution.png" + ).exists(), "Plot 'lift_distribution.png' does not exist." + + +def test_get_avl_aerocoefs(): + assert FT_TEMPLATE.exists(), "Result file 'ft.txt' not found!" + cl, cd, cm = get_avl_aerocoefs(FT_TEMPLATE) + assert cl == pytest.approx(0.35063, rel=1e-4), "CLtot is not correct!" + assert cd == pytest.approx(0.00624, rel=1e-4), "CDtot is not correct!" + assert cm == pytest.approx(-0.01362, rel=1e-4), "Cmtot is not correct!" + + +# ================================================================================================= +# MAIN +# ================================================================================================= + +if __name__ == "__main__": + print("Test avlconfig.py") + print("To run test use the following command:") + print(">> pytest -v") diff --git a/ceasiompy/SU2Run/__specs__.py b/ceasiompy/SU2Run/__specs__.py index 243ad926b..8a009fae7 100644 --- a/ceasiompy/SU2Run/__specs__.py +++ b/ceasiompy/SU2Run/__specs__.py @@ -327,7 +327,7 @@ cpacs_inout.add_input( var_name="update_wetted_area", var_type=bool, - default_value=False, + default_value=True, unit="1", descr="Option to update the wetted area from the latest SU2 result.", xpath=SU2_UPDATE_WETTED_AREA_XPATH, diff --git a/ceasiompy/SU2Run/files/config_template_euler.cfg b/ceasiompy/SU2Run/files/config_template_euler.cfg new file mode 100644 index 000000000..d4b35df00 --- /dev/null +++ b/ceasiompy/SU2Run/files/config_template_euler.cfg @@ -0,0 +1,411 @@ +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% +% % +% SU2 configuration file % +% Case description: Template for euler simulations based on ONERA M6 case % +% Author: G.Benedetti % +% Institution: CFS Engineering % +% Date: 2024.06.03 % +% File Version 7.3.0 "Blackbird" % +% % +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% + +% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% +% +% Physical governing equations (EULER, NAVIER_STOKES) +SOLVER= EULER +% +% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT) +MATH_PROBLEM= DIRECT +% +% Restart solution (NO, YES) +RESTART_SOL= YES +% +% Read binary restart files (YES, NO) +READ_BINARY_RESTART= NO +% + +% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% +% +% Mach number (non-dimensional, based on the free-stream values) +MACH_NUMBER= 0.8395 +% +% Angle of attack (degrees) +AOA= 3.06 +% +% Side-slip angle (degrees) +SIDESLIP_ANGLE= 0.0 +% +% Free-stream pressure (101325.0 N/m^2 by default, only for Euler equations) +FREESTREAM_PRESSURE= 101325.0 +% +% Free-stream temperature (288.15 K by default) +FREESTREAM_TEMPERATURE= 288.15 + +% ---------------------- REFERENCE VALUE DEFINITION ---------------------------% +% +% Reference origin for moment computation +REF_ORIGIN_MOMENT_X = 0.25 +REF_ORIGIN_MOMENT_Y = 0.00 +REF_ORIGIN_MOMENT_Z = 0.00 +% +% Reference length for pitching, rolling, and yaMAIN_BOX non-dimensional moment +REF_LENGTH= 1.0 +% +% Reference area for force coefficients (0 implies automatic calculation) +REF_AREA= 0 +% +% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE, +% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE) +REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_ONE + +% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------% +% +% Marker of the Euler boundary (0 implies no marker) +MARKER_EULER= ( WING ) +% +% Marker of the far field (0 implies no marker) +MARKER_FAR= ( FARFIELD ) +% +% Marker of symmetry boundary (0 implies no marker) +MARKER_SYM= ( SYMMETRY ) + +% ------------------------ SURFACES IDENTIFICATION ----------------------------% +% +% Marker(s) of the surface in the surface flow solution file +MARKER_PLOTTING = ( WING ) +% +% Marker(s) of the surface where the non-dimensional coefficients are evaluated. +MARKER_MONITORING = ( WING ) +% +% Marker(s) of the surface where obj. func. (design problem) will be evaluated +MARKER_DESIGNING = ( WING ) + +% ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------% +% +% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES) +NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES +% +% Objective function in gradient evaluation (DRAG, LIFT, SIDEFORCE, MOMENT_X, +% MOMENT_Y, MOMENT_Z, EFFICIENCY, +% EQUIVALENT_AREA, NEARFIELD_PRESSURE, +% FORCE_X, FORCE_Y, FORCE_Z, THRUST, +% TORQUE, FREE_SURFACE, TOTAL_HEATFLUX, +% MAXIMUM_HEATFLUX, INVERSE_DESIGN_PRESSURE, +% INVERSE_DESIGN_HEATFLUX) +OBJECTIVE_FUNCTION= DRAG +% +% Courant-Friedrichs-Lewy condition of the finest grid +CFL_NUMBER= 5.0 +% +% Adaptive CFL number (NO, YES) +CFL_ADAPT= NO +% +% Parameters of the adaptive CFL number (factor down, factor up, CFL min value, +% CFL max value ) +CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 ) +% +% Runge-Kutta alpha coefficients +RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) +% +% Number of total iterations +ITER= 99999 +% +% Linear solver for the implicit formulation (BCGSTAB, FGMRES) +LINEAR_SOLVER= FGMRES +% +% Preconditioner of the Krylov linear solver (ILU, LU_SGS, LINELET, JACOBI) +LINEAR_SOLVER_PREC= LU_SGS +% +% Min error of the linear solver for the implicit formulation +LINEAR_SOLVER_ERROR= 1E-6 +% +% Max number of iterations of the linear solver for the implicit formulation +LINEAR_SOLVER_ITER= 2 + +% ----------------------- SLOPE LIMITER DEFINITION ----------------------------% +% +% Coefficient for the limiter +VENKAT_LIMITER_COEFF= 0.03 +% +% Coefficient for the sharp edges limiter +ADJ_SHARP_LIMITER_COEFF= 3.0 +% +% Reference coefficient (sensitivity) for detecting sharp edges. +REF_SHARP_EDGES= 3.0 +% +% Remove sharp edges from the sensitivity evaluation (NO, YES) +SENS_REMOVE_SHARP= YES + +% -------------------------- MULTIGRID PARAMETERS -----------------------------% +% +% Multi-Grid Levels (0 = no multi-grid) +MGLEVEL= 3 +% +% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE) +MGCYCLE= W_CYCLE +% +% Multi-Grid PreSmoothing Level +MG_PRE_SMOOTH= ( 1, 2, 3, 3 ) +% +% Multi-Grid PostSmoothing Level +MG_POST_SMOOTH= ( 0, 0, 0, 0 ) +% +% Jacobi implicit smoothing of the correction +MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 ) +% +% Damping factor for the residual restriction +MG_DAMP_RESTRICTION= 0.9 +% +% Damping factor for the correction prolongation +MG_DAMP_PROLONGATION= 0.9 + +% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% +% +% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC, +% TURKEL_PREC, MSW) +CONV_NUM_METHOD_FLOW= JST +% +% Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations. +% Required for 2nd order upwind schemes (NO, YES) +MUSCL_FLOW= YES +% +% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG, +% BARTH_JESPERSEN, VAN_ALBADA_EDGE) +SLOPE_LIMITER_FLOW= NONE +% +% 2nd and 4th order artificial dissipation coefficients +JST_SENSOR_COEFF= ( 0.5, 0.02 ) +% +% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT) +TIME_DISCRE_FLOW= EULER_IMPLICIT + +% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------% +% +% Convective numerical method (JST, LAX-FRIEDRICH, ROE) +CONV_NUM_METHOD_ADJFLOW= JST +% +% Monotonic Upwind Scheme for Conservation Laws (TVD) in the adjoint flow equations. +% Required for 2nd order upwind schemes (NO, YES) +MUSCL_ADJFLOW= YES +% +% Slope limiter (NONE, VENKATAKRISHNAN, BARTH_JESPERSEN, VAN_ALBADA_EDGE, +% SHARP_EDGES, WALL_DISTANCE) +SLOPE_LIMITER_ADJFLOW= NONE +% +% 2nd, and 4th order artificial dissipation coefficients +ADJ_JST_SENSOR_COEFF= ( 0.0, 0.02 ) +% +% Reduction factor of the CFL coefficient in the adjoint problem +CFL_REDUCTION_ADJFLOW= 0.5 +% +% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT) +TIME_DISCRE_ADJFLOW= EULER_IMPLICIT + +% --------------------------- CONVERGENCE PARAMETERS --------------------------& +% +% Min value of the residual (log10 of the residual) +CONV_RESIDUAL_MINVAL= -12 +% +% Start convergence criteria at iteration number +CONV_STARTITER= 25 +% +% Number of elements to apply the criteria +CONV_CAUCHY_ELEMS= 100 +% +% Epsilon to control the series convergence +CONV_CAUCHY_EPS= 1E-10 +% + +% ------------------------- INPUT/OUTPUT INFORMATION --------------------------% +% +% Mesh input file +MESH_FILENAME= mesh_ONERAM6_inv_ffd.su2 +% +% Mesh output file +MESH_OUT_FILENAME= mesh_out.su2 +% +% Restart flow input file +SOLUTION_FILENAME= solution_flow.dat +% +% Restart adjoint input file +SOLUTION_ADJ_FILENAME= solution_adj.dat +% +% Mesh input file format (SU2) +MESH_FORMAT= SU2 +% +TABULAR_FORMAT= CSV +% +% Output file convergence history +CONV_FILENAME= history +% +% Output file restart flow +RESTART_FILENAME= restart_flow.dat +% +% Output file restart adjoint +RESTART_ADJ_FILENAME= restart_adj.dat +% +% Output file flow (w/o extension) variables +VOLUME_FILENAME= flow +% +% Output file adjoint (w/o extension) variables +VOLUME_ADJ_FILENAME= adjoint +% +% Output Objective function gradient (using continuous adjoint) +GRAD_OBJFUNC_FILENAME= of_grad.dat +% +% Output file surface flow coefficient (w/o extension) +SURFACE_FILENAME= surface_flow +% +% Output file surface adjoint coefficient (w/o extension) +SURFACE_ADJ_FILENAME= surface_adjoint +% +% Writing solution frequency +OUTPUT_WRT_FREQ= 100 +% +% +% Screen output fields +SCREEN_OUTPUT = (INNER_ITER, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG) +% +OUTPUT_FILES= (RESTART_ASCII, CGNS, SURFACE_CGNS) +% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------% +% +% Kind of deformation (TRANSLATION, ROTATION, SCALE, +% FFD_SETTING, +% FFD_CONTROL_POINT, FFD_CAMBER, FFD_THICKNESS +% FFD_NACELLE, FFD_TWIST, FFD_ROTATION, +% FFD_CONTROL_POINT_2D, FFD_CAMBER_2D, FFD_THICKNESS_2D, +% HICKS_HENNE, PARABOLIC, NACA_4DIGITS, AIRFOIL) +DV_KIND= FFD_CONTROL_POINT +% +% Marker of the surface in which we are going apply the shape deformation +DV_MARKER= ( WING ) +% +% Parameters of the shape deformation +% - TRANSLATION ( x_Disp, y_Disp, z_Disp ), as a unit vector +% - ROTATION ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) +% - SCALE ( 1.0 ) +% - FFD_SETTING ( 1.0 ) +% - FFD_CONTROL_POINT ( FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Disp, y_Disp, z_Disp ) +% - FFD_CAMBER ( FFD_BoxTag, i_Ind, j_Ind ) +% - FFD_THICKNESS ( FFD_BoxTag, i_Ind, j_Ind ) +% - FFD_TWIST_ANGLE ( FFD_BoxTag, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) +% - FFD_ROTATION ( FFD_BoxTag, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) +% - FFD_CONTROL_POINT_2D ( FFD_BoxTag, i_Ind, j_Ind, x_Disp, y_Disp ) +% - FFD_CAMBER_2D ( FFD_BoxTag, i_Ind ) +% - FFD_THICKNESS_2D ( FFD_BoxTag, i_Ind ) +% - HICKS_HENNE ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), x_Loc ) +% - PARABOLIC ( Center, Thickness ) +% - NACA_4DIGITS ( 1st digit, 2nd digit, 3rd and 4th digit ) +% - AIRFOIL ( 1.0 ) +DV_PARAM= ( MAIN_BOX, 2, 3, 1, 0.0, 0.0, 1.0 ) +% +% Value of the shape deformation +DV_VALUE= 0.05 + +% ------------------------ GRID DEFORMATION PARAMETERS ------------------------% +% +% Linear solver or smoother for implicit formulations (FGMRES, RESTARTED_FGMRES, +% BCGSTAB) +DEFORM_LINEAR_SOLVER= FGMRES +% +% Number of smoothing iterations for mesh deformation +DEFORM_LINEAR_SOLVER_ITER= 500 +% +% Number of nonlinear deformation iterations (surface deformation increments) +DEFORM_NONLINEAR_ITER= 2 +% +% Print the residuals during mesh deformation to the console (YES, NO) +DEFORM_CONSOLE_OUTPUT= NO +% +% Minimum residual criteria for the linear solver convergence of grid deformation +DEFORM_LINEAR_SOLVER_ERROR= 1E-14 +% +% Type of element stiffness imposed for FEA mesh deformation (INVERSE_VOLUME, +% WALL_DISTANCE, CONSTANT_STIFFNESS) +DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME + +% -------------------- FREE-FORM DEFORMATION PARAMETERS -----------------------% +% +% Tolerance of the Free-Form Deformation point inversion +FFD_TOLERANCE= 1E-10 +% +% Maximum number of iterations in the Free-Form Deformation point inversion +FFD_ITERATIONS= 500 +% +% FFD box definition: 3D case (FFD_BoxTag, X1, Y1, Z1, X2, Y2, Z2, X3, Y3, Z3, X4, Y4, Z4, +% X5, Y5, Z5, X6, Y6, Z6, X7, Y7, Z7, X8, Y8, Z8) +% 2D case (FFD_BoxTag, X1, Y1, 0.0, X2, Y2, 0.0, X3, Y3, 0.0, X4, Y4, 0.0, +% 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0) +FFD_DEFINITION= (MAIN_BOX, -0.0403, 0.0, -0.04836, 0.8463, 0.0, -0.04836, 1.209, 1.2896, -0.04836, 0.6851, 1.2896, -0.04836, -0.0403, 0.0, 0.04836, 0.8463, 0.0, 0.04836, 1.209, 1.2896, 0.04836, 0.6851, 1.2896, 0.04836) +% +% FFD box degree: 3D case (x_degree, y_degree, z_degree) +% 2D case (x_degree, y_degree, 0) +FFD_DEGREE= (10, 8, 1) +% +% Surface continuity at the intersection with the FFD (1ST_DERIVATIVE, 2ND_DERIVATIVE) +FFD_CONTINUITY= 2ND_DERIVATIVE + +% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------% +% +% Available flow based objective functions or constraint functions +% DRAG, LIFT, SIDEFORCE, EFFICIENCY, BUFFET, +% FORCE_X, FORCE_Y, FORCE_Z, +% MOMENT_X, MOMENT_Y, MOMENT_Z, +% THRUST, TORQUE, FIGURE_OF_MERIT, +% EQUIVALENT_AREA, NEARFIELD_PRESSURE, +% TOTAL_HEATFLUX, MAXIMUM_HEATFLUX, +% INVERSE_DESIGN_PRESSURE, INVERSE_DESIGN_HEATFLUX, +% SURFACE_TOTAL_PRESSURE, SURFACE_MASSFLOW +% SURFACE_STATIC_PRESSURE, SURFACE_MACH +% +% Available geometrical based objective functions or constraint functions +% AIRFOIL_AREA, AIRFOIL_THICKNESS, AIRFOIL_CHORD, AIRFOIL_TOC, AIRFOIL_AOA, +% WING_VOLUME, WING_MIN_THICKNESS, WING_MAX_THICKNESS, WING_MAX_CHORD, WING_MIN_TOC, WING_MAX_TWIST, WING_MAX_CURVATURE, WING_MAX_DIHEDRAL +% STATION#_WIDTH, STATION#_AREA, STATION#_THICKNESS, STATION#_CHORD, STATION#_TOC, +% STATION#_TWIST (where # is the index of the station defined in GEO_LOCATION_STATIONS) +% +% Available design variables +% 2D Design variables +% FFD_CONTROL_POINT_2D ( 19, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind, x_Mov, y_Mov ) +% FFD_CAMBER_2D ( 20, Scale | Mark. List | FFD_BoxTag, i_Ind ) +% FFD_THICKNESS_2D ( 21, Scale | Mark. List | FFD_BoxTag, i_Ind ) +% FFD_TWIST_2D ( 22, Scale | Mark. List | FFD_BoxTag, x_Orig, y_Orig ) +% HICKS_HENNE ( 30, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc ) +% ANGLE_OF_ATTACK ( 101, Scale | Mark. List | 1.0 ) +% +% 3D Design variables +% FFD_CONTROL_POINT ( 11, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Mov, y_Mov, z_Mov ) +% FFD_NACELLE ( 12, Scale | Mark. List | FFD_BoxTag, rho_Ind, theta_Ind, phi_Ind, rho_Mov, phi_Mov ) +% FFD_GULL ( 13, Scale | Mark. List | FFD_BoxTag, j_Ind ) +% FFD_CAMBER ( 14, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind ) +% FFD_TWIST ( 15, Scale | Mark. List | FFD_BoxTag, j_Ind, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) +% FFD_THICKNESS ( 16, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind ) +% FFD_ROTATION ( 18, Scale | Mark. List | FFD_BoxTag, x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn ) +% FFD_ANGLE_OF_ATTACK ( 24, Scale | Mark. List | FFD_BoxTag, 1.0 ) +% +% Global design variables +% TRANSLATION ( 1, Scale | Mark. List | x_Disp, y_Disp, z_Disp ) +% ROTATION ( 2, Scale | Mark. List | x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn ) +% +% Optimization objective function with scaling factor +% ex= Objective * Scale +OPT_OBJECTIVE= DRAG * 1.0 +% +% Optimization constraint functions with scaling factors, separated by semicolons +% ex= (Objective = Value ) * Scale, use '>','<','=' +OPT_CONSTRAINT= ( LIFT > 0.282557 ) * 1.0 +% +% Maximum number of iterations +OPT_ITERATIONS= 100 +% +% Requested accuracy +OPT_ACCURACY= 1E-6 +% +% Upper bound for each design variable +OPT_BOUND_UPPER= 0.1 +% +% Lower bound for each design variable +OPT_BOUND_LOWER= -0.1 +% +% Optimization design variables, separated by semicolons +DEFINITION_DV= ( 11, 1.0 | WING | MAIN_BOX, 0, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 3, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 4, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 5, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 6, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 7, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 8, 0, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 3, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 4, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 5, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 6, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 7, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 0, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 1, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 2, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 3, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 4, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 5, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 6, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 7, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 8, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 9, 8, 1, 0.0, 0.0, 1.0 ); ( 11, 1.0 | WING | MAIN_BOX, 10, 8, 1, 0.0, 0.0, 1.0 ) diff --git a/ceasiompy/SU2Run/func/su2utils.py b/ceasiompy/SU2Run/func/su2utils.py index 24db788bf..b815cb012 100644 --- a/ceasiompy/SU2Run/func/su2utils.py +++ b/ceasiompy/SU2Run/func/su2utils.py @@ -79,7 +79,6 @@ def get_mesh_markers(su2_mesh_path): lines = f.readlines() for line in lines: - if "MARKER_TAG" not in line: continue @@ -129,7 +128,6 @@ def get_su2_version(): with open(su2py_path, "r") as f: for line in f.readlines(): - if "version" not in line: continue @@ -141,37 +139,38 @@ def get_su2_version(): def get_su2_config_template(): """Return path of the SU2 config template corresponding to the SU2 version.""" - su2_version = get_su2_version() + # su2_version = get_su2_version() su2_dir = get_module_path("SU2Run") - su2_config_template_path = Path(su2_dir, "files", f"config_template_v{su2_version}.cfg") + su2_config_template_path_euler = Path(su2_dir, "files", "config_template_euler.cfg") - if not su2_config_template_path.exists(): + # su2_config_template_path = Path(su2_dir, "files", f"config_template_v{su2_version}.cfg") - # Use the Euler Onera M6 config as template - url = ( - f"https://raw.githubusercontent.com/su2code/SU2/v{su2_version}" - "/TestCases/euler/oneram6/inv_ONERAM6.cfg" - ) - r = requests.get(url) + # if not su2_config_template_path.exists(): - if r.status_code == 404: - raise FileNotFoundError( - f"The SU2 config template for SU2 version {su2_version} does not exist." - ) + # # Use the Euler Onera M6 config as template + # url = ( + # f"https://raw.githubusercontent.com/su2code/SU2/v{su2_version}" + # "/TestCases/euler/oneram6/inv_ONERAM6.cfg" + # ) + # r = requests.get(url) - if not r.status_code == 200: - raise ConnectionError( - f"Cannot download the template file for SU2 version {su2_version} at {url}" - ) + # if r.status_code == 404: + # raise FileNotFoundError( + # f"The SU2 config template for SU2 version {su2_version} does not exist." + # ) - with open(su2_config_template_path, "wb") as f: - f.write(r.content) + # if not r.status_code == 200: + # raise ConnectionError( + # f"Cannot download the template file for SU2 version {su2_version} at {url}" + # ) - return su2_config_template_path + # with open(su2_config_template_path, "wb") as f: + # f.write(r.content) + return su2_config_template_path_euler -def get_su2_config_template_rans(): +def get_su2_config_template_rans(): su2_dir = get_module_path("SU2Run") su2_config_template_path_rans = Path(su2_dir, "files", "config_template_rans.cfg") @@ -296,5 +295,4 @@ def get_wetted_area(su2_logfile): # ================================================================================================= if __name__ == "__main__": - print("Nothing to execute!") diff --git a/ceasiompy/SU2Run/tests/tests_su2utils/test_su2utils.py b/ceasiompy/SU2Run/tests/tests_su2utils/test_su2utils.py index f41a80a95..648fe8eac 100644 --- a/ceasiompy/SU2Run/tests/tests_su2utils/test_su2utils.py +++ b/ceasiompy/SU2Run/tests/tests_su2utils/test_su2utils.py @@ -125,20 +125,16 @@ def test_get_su2_config_template(): su2_dir = get_module_path("SU2Run") # Test with an old version of the config template - su2_version = "3.0.0" - config_template_path = Path(su2_dir, "files", f"config_template_v{su2_version}.cfg") + config_template_path = Path(su2_dir, "files", "config_template_euler.cfg") # Remove the config template file if it exists (from a previous test) if config_template_path.exists(): - config_template_path.unlink() - - with patch("ceasiompy.SU2Run.func.su2utils.get_su2_version", return_value=su2_version): assert get_su2_config_template() == config_template_path - # Test with an inexistent config template version - with patch("ceasiompy.SU2Run.func.su2utils.get_su2_version", return_value="9.9.99"): - with pytest.raises(FileNotFoundError): - assert get_su2_config_template() == config_template_path + # # Test with an inexistent config template version + # with patch("ceasiompy.SU2Run.func.su2utils.get_su2_version", return_value="9.9.99"): + # with pytest.raises(FileNotFoundError): + # assert get_su2_config_template() == config_template_path def test_get_su2_aerocoefs(): diff --git a/ceasiompy/utils/commonxpath.py b/ceasiompy/utils/commonxpath.py index 82e0f8393..ca30c6492 100644 --- a/ceasiompy/utils/commonxpath.py +++ b/ceasiompy/utils/commonxpath.py @@ -209,3 +209,10 @@ # PYCYCLE ENGINE_TYPE_XPATH = CEASIOMPY_XPATH + "/ThermoData" ENGINE_BC = CEASIOMPY_XPATH + "/BC" + +# AVL +AVL_XPATH = CEASIOMPY_XPATH + "/aerodynamics/avl" +AVL_AEROMAP_UID_XPATH = AVL_XPATH + "/aeroMapUID" +AVL_PLOT_XPATH = AVL_XPATH + "/SavePlots" +AVL_FUSELAGE_XPATH = AVL_XPATH + "/IntegrateFuselage" +AVL_VORTEX_DISTR_XPATH = AVL_XPATH + "/VortexDistribution" diff --git a/environment.yml b/environment.yml index d798c246f..29ffcb143 100644 --- a/environment.yml +++ b/environment.yml @@ -37,14 +37,16 @@ dependencies: - vtk=9.0.1 - pip: + - altair == 4.0.0 - ambiance==1.3.0 - black==22.3 - cpacspy==0.1.8 - cython==0.29.30 - gmsh==4.10.3 - markdownpy==0.1.4 + - om-pycycle - pytest==7.2.0 - smt==1.2.0 - streamlit==1.14.0 - streamlit-autorefresh - - om-pycycle + diff --git a/installation/CentOS/install_pyavl.sh b/installation/CentOS/install_pyavl.sh new file mode 100755 index 000000000..346618421 --- /dev/null +++ b/installation/CentOS/install_pyavl.sh @@ -0,0 +1,30 @@ +#!/bin/bash + +# Script to install avl on CentOS + +current_dir="$(pwd)" + +if [ $# -gt 0 ]; then + install_dir="$1/INSTALLDIR" +else + install_dir="$(pwd)/../../INSTALLDIR" +fi + +echo "Creating install directory..." +mkdir -p "$install_dir" +cd "$install_dir" + +echo "Downloading AVL..." +wget -q https://web.mit.edu/drela/Public/web/avl/avl3.40_execs/LINUX64/avl \ +|| { echo "Error: Failed to download AVL." >&2; exit 1; } + + +chmod +x avl || { echo "Error: Failed to set execute permission on AVL binary." >&2; exit 1; } + +sudo dnf install -y ghostscript + +echo "export PATH=\"\$PATH:$install_dir\"" >> ~/.bashrc + +cd "$current_dir" + +echo "AVL installed successfully in $install_dir and added to PATH." diff --git a/installation/CentOS/install_sumo.sh b/installation/CentOS/install_sumo.sh old mode 100644 new mode 100755 diff --git a/installation/INSTALLATION.md b/installation/INSTALLATION.md index 096a1dd3e..2552e9084 100644 --- a/installation/INSTALLATION.md +++ b/installation/INSTALLATION.md @@ -38,6 +38,7 @@ cd CEASIOMpy/installation/Ubuntu ./install_miniconda.sh source ~/.bashrc ./install_ceasiompy.sh +./install_pyavl.sh ./install_pytornado.sh ./install_sumo.sh ./install_su2.sh @@ -54,6 +55,7 @@ cd CEASIOMpy/installation/CentOS ./install_miniconda.sh source ~/.bashrc ./install_ceasiompy.sh +./install_pyavl.sh ./install_pytornado.sh ./install_sumo.sh ./install_su2.sh @@ -67,6 +69,7 @@ When it is done, you can test the installation, by opening a new terminal and tr conda activate ceasiompy python -c "import ceasiompy" cpacscreator # A "CPACSCreator" window will open, you can close it. +avl # The avl interface should appear in the terminal pytornado # You should see the help of PyTornado in the terminal. sumo # A "SUMO" window will open, you can close it. SU2_CFD # You should see something like "Error in "void CConfig::SetConfig_Parsing(char*)" in the terminal @@ -95,6 +98,7 @@ You can try to install it manually, the basic steps are the following: - Run the command `pip install -e .` - Install [PyTornado](https://github.com/airinnova/pytornado) - Install [SUMO](https://www.larosterna.com/products/open-source) +- Install [AVL](https://web.mit.edu/drela/Public/web/avl) - Install [SU2](https://su2code.github.io/download.html) - Install [Paraview](https://www.paraview.org/download/) @@ -111,6 +115,7 @@ You can install it manually, the basic steps are the following: - Run the command `pip install -e .` - Install [PyTornado](https://github.com/airinnova/pytornado) - Install [SUMO](https://www.larosterna.com/products/open-source) +- Install [AVL](https://web.mit.edu/drela/Public/web/avl) - Install [SU2](https://su2code.github.io/download.html) - Install [Paraview](https://www.paraview.org/download/) diff --git a/installation/Ubuntu/install_pyavl.sh b/installation/Ubuntu/install_pyavl.sh new file mode 100755 index 000000000..d86eb066a --- /dev/null +++ b/installation/Ubuntu/install_pyavl.sh @@ -0,0 +1,32 @@ +#!/bin/bash + +# Script to install avl on Ubuntu 20.04 and Mint 20.3 + +current_dir="$(pwd)" + +if [ $# -gt 0 ]; then + install_dir="$1/INSTALLDIR" +else + install_dir="$(pwd)/../../INSTALLDIR" +fi + +echo "Creating install directory..." +mkdir -p "$install_dir" +cd "$install_dir" + +echo "Downloading AVL..." +wget -q https://web.mit.edu/drela/Public/web/avl/avl3.40_execs/LINUX64/avl \ +|| { echo "Error: Failed to download AVL." >&2; exit 1; } + + +chmod +x avl || { echo "Error: Failed to set execute permission on AVL binary." >&2; exit 1; } + +echo "export PATH=\"\$PATH:$install_dir\"" >> ~/.bashrc + +sudo apt-get install -y ghostscript + +ps2pdf + +cd "$current_dir" + +echo "AVL installed successfully in $install_dir and added to PATH." diff --git "a/src/streamlit/pages/01_ \342\236\241_Workflow.py" "b/src/streamlit/pages/01_ \342\236\241_Workflow.py" index ac987512f..1a3ad7510 100644 --- "a/src/streamlit/pages/01_ \342\236\241_Workflow.py" +++ "b/src/streamlit/pages/01_ \342\236\241_Workflow.py" @@ -64,7 +64,7 @@ def section_predefined_workflow(): st.markdown("#### Predefined Workflows") predefine_workflows = [ - ["PyTornado", "WeightConventional"], + ["PyAVL", "SaveAeroCoefficients"], ["CPACS2GMSH", "SU2Run", "SkinFriction"], ["CPACS2GMSH", "ThermoData", "SU2Run"], ["CPACS2SUMO", "SUMOAutoMesh", "SU2Run", "ExportCSV"], diff --git a/test_files/CPACSfiles/DC2_Reference_T34_230517_v3.1.xml b/test_files/CPACSfiles/DC2_Reference_T34_230517_v3.1.xml new file mode 100644 index 000000000..668466415 --- /dev/null +++ b/test_files/CPACSfiles/DC2_Reference_T34_230517_v3.1.xml @@ -0,0 +1,6369 @@ + + +
+ AGILE_DC-2_Reference_T33 + 1.1 + 3.0 + AGILE WP3 T33 + AGILE D3.1 Reference aircraft for hi fi + 2017-03-07T20:51:00 + + + Initial Synthesis + TUD + + + CIAM Reference Engine included + DLR + + + POLITO Systems Mass analysis included + DLR + + + UNINA High Lift design included + DLR + + + Structural components included + DLR + + + DLR updated synthesis L0 + DLR + + + DLR major update for AGILE T3.3 hi-fi needs + DLR + + + Changed rudder values for 3.4, added 3.4 tool specific, added rudder actuator data + Fokker + + + Changed the rudder start to 0% of the vertical + Fokker + + + Converted to cpacs 3.0 using cpacs2to3 + cpacs2to3 + 2018-10-26T16:16:55 + ver1 + 3.0 + + + Replaced aeroPerformanceMap by aeroMap. Removed toolspecifics. + CFSE + 2020-03-06 15:35:29.645940 + 3.0 + + +
+ + + + AGILE-DC2-T33 + Agile DC2: 2:2 abreast 9180kg, right fuselage dims, medium BPR engine (6), max payload+range mission, LFL 1400 and TOFL 1500m, increased CLmax values + + + 0.0 + 0.0 + 15.6949 + + 3.7317 + 82.7 + + + + NASA_CRM_fuselage1 + NASA_CRM_fuselage1 model + + + 0.55 + 0.48 + 0.48 + + + 0.0 + 0.0 + 0.0 + + + -1.3 + 0.0 + -2.7 + + + +
+ NASA_CRM_Fus1_sec1 + NASA_CRM_Fus1_sec1 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 2.3595 + 0.0 + 4.932391 + + + + + NASA_CRM_fus1_sec1_Elem1 + NASA_CRM_fus1_sec1_Elem1 + NASA_CRM_fus1_profile1 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + +
+
+ NASA_CRM_Fus1_sec2 + NASA_CRM_Fus1_sec2 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 2.3795 + 0.0 + 4.860254 + + + + + NASA_CRM_fus1_sec2_Elem1 + NASA_CRM_fus1_sec2_Elem1 + NASA_CRM_fus1_profile2 + + + 0.338466 + 0.338466 + 0.338466 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + +
+
+ NASA_CRM_Fus1_sec3 + NASA_CRM_Fus1_sec3 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 2.4295 + 0.0 + 4.752808 + + + + + NASA_CRM_fus1_sec3_Elem1 + NASA_CRM_fus1_sec3_Elem1 + NASA_CRM_fus1_profile3 + + + 0.55414 + 0.55414 + 0.55414 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + +
+
+ NASA_CRM_Fus1_sec4 + NASA_CRM_Fus1_sec4 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 2.6695 + 0.0 + 4.479785 + + + + + NASA_CRM_fus1_sec4_Elem1 + NASA_CRM_fus1_sec4_Elem1 + NASA_CRM_fus1_profile4 + + + 1.113595 + 1.113595 + 1.113595 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + +
+
+ NASA_CRM_Fus1_sec5 + NASA_CRM_Fus1_sec5 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 3.2815 + 0.0 + 4.112995 + + + + + NASA_CRM_fus1_sec5_Elem1 + NASA_CRM_fus1_sec5_Elem1 + NASA_CRM_fus1_profile5 + + + 1.920177 + 1.920177 + 1.920177 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + +
+
+ NASA_CRM_Fus1_sec6 + NASA_CRM_Fus1_sec6 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 3.7555 + 0.0 + 3.892743 + + + + + NASA_CRM_fus1_sec6_Elem1 + NASA_CRM_fus1_sec6_Elem1 + NASA_CRM_fus1_profile6 + + + 2.518746 + 2.518746 + 2.518746 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + +
+
+ NASA_CRM_Fus1_sec7 + NASA_CRM_Fus1_sec7 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 4.0905 + 0.0 + 3.752841 + + + + + NASA_CRM_fus1_sec7_Elem1 + NASA_CRM_fus1_sec7_Elem1 + NASA_CRM_fus1_profile7 + + + 2.984681 + 2.984681 + 2.984681 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + +
+
+ NASA_CRM_Fus1_sec8 + NASA_CRM_Fus1_sec8 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 4.8975 + 0.0 + 3.46156 + + + + + NASA_CRM_fus1_sec8_Elem1 + NASA_CRM_fus1_sec8_Elem1 + NASA_CRM_fus1_profile8 + + + 3.76646 + 3.76646 + 3.76646 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + +
+
+ NASA_CRM_Fus1_sec9 + NASA_CRM_Fus1_sec9 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 6.6005 + 0.0 + 3.010557 + + + + + NASA_CRM_fus1_sec9_Elem1 + NASA_CRM_fus1_sec9_Elem1 + NASA_CRM_fus1_profile9 + + + 4.812545 + 4.812545 + 4.812545 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + +
+
+ NASA_CRM_Fus1_sec10 + NASA_CRM_Fus1_sec10 + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + 8.7865 + 0.0 + 2.656317 + + + + + NASA_CRM_fus1_sec10_Elem1 + NASA_CRM_fus1_sec10_Elem1 + NASA_CRM_fus1_profile10 + + + 5.671808 + 5.671808 + 5.671808 + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + +
+
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+
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+
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+
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+
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+
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+
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+
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+
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+
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OptimaleBL3_Fuselage_Sec6 + + + 216.503 + 90 + 0 + OptimaleBL3 - Fuselage Section 7 Positioning + OptimaleBL3 - Fuselage Section 7 Positioning + OptimaleBL3_Fuselage_Sec6 + OptimaleBL3_Fuselage_Sec7 + + + 252.837 + 90 + 0 + OptimaleBL3 - Fuselage Section 8 Positioning + OptimaleBL3 - Fuselage Section 8 Positioning + OptimaleBL3_Fuselage_Sec7 + OptimaleBL3_Fuselage_Sec8 + + + 287.687 + 90 + 0 + OptimaleBL3 - Fuselage Section 9 Positioning + OptimaleBL3 - Fuselage Section 9 Positioning + OptimaleBL3_Fuselage_Sec8 + OptimaleBL3_Fuselage_Sec9 + + + 320.849 + 90 + 0 + OptimaleBL3 - Fuselage Section 10 Positioning + OptimaleBL3 - Fuselage Section 10 Positioning + OptimaleBL3_Fuselage_Sec9 + OptimaleBL3_Fuselage_Sec10 + + + 352.128 + 90 + 0 + OptimaleBL3 - Fuselage Section 11 Positioning + OptimaleBL3 - Fuselage Section 11 Positioning + OptimaleBL3_Fuselage_Sec10 + OptimaleBL3_Fuselage_Sec11 + + + 381.341 + 90 + 0 + OptimaleBL3 - Fuselage Section 12 Positioning + OptimaleBL3 - Fuselage Section 12 Positioning + OptimaleBL3_Fuselage_Sec11 + OptimaleBL3_Fuselage_Sec12 + + + 408.316 + 90 + 0 + OptimaleBL3 - Fuselage Section 13 Positioning + OptimaleBL3 - Fuselage Section 13 Positioning + OptimaleBL3_Fuselage_Sec12 + OptimaleBL3_Fuselage_Sec13 + + + 432.895 + 90 + 0 + OptimaleBL3 - Fuselage Section 14 Positioning + OptimaleBL3 - Fuselage Section 14 Positioning + OptimaleBL3_Fuselage_Sec13 + OptimaleBL3_Fuselage_Sec14 + + + 454.933 + 90 + 0 + OptimaleBL3 - Fuselage Section 15 Positioning + OptimaleBL3 - Fuselage Section 15 Positioning + OptimaleBL3_Fuselage_Sec14 + OptimaleBL3_Fuselage_Sec15 + + + 474.302 + 90 + 0 + OptimaleBL3 - Fuselage Section 16 Positioning + OptimaleBL3 - Fuselage Section 16 Positioning + OptimaleBL3_Fuselage_Sec15 + OptimaleBL3_Fuselage_Sec16 + + + 490.887 + 90 + 0 + OptimaleBL3 - Fuselage Section 17 Positioning + OptimaleBL3 - Fuselage Section 17 Positioning + OptimaleBL3_Fuselage_Sec16 + OptimaleBL3_Fuselage_Sec17 + + + 504.592 + 90 + 0 + OptimaleBL3 - Fuselage Section 18 Positioning + OptimaleBL3 - Fuselage Section 18 Positioning + OptimaleBL3_Fuselage_Sec17 + OptimaleBL3_Fuselage_Sec18 + + + 515.335 + 90 + 0 + OptimaleBL3 - Fuselage Section 19 Positioning + OptimaleBL3 - Fuselage Section 19 Positioning + OptimaleBL3_Fuselage_Sec18 + OptimaleBL3_Fuselage_Sec19 + + + 523.055 + 90 + 0 + OptimaleBL3 - Fuselage Section 20 Positioning + OptimaleBL3 - Fuselage Section 20 Positioning + OptimaleBL3_Fuselage_Sec19 + OptimaleBL3_Fuselage_Sec20 + + + 527.704 + 90 + 0 + OptimaleBL3 - Fuselage Section 21 Positioning + OptimaleBL3 - Fuselage Section 21 Positioning + OptimaleBL3_Fuselage_Sec20 + OptimaleBL3_Fuselage_Sec21 + + + 529.257 + 90 + 0 + OptimaleBL3 - Fuselage Section 22 Positioning + OptimaleBL3 - Fuselage Section 22 Positioning + OptimaleBL3_Fuselage_Sec21 + OptimaleBL3_Fuselage_Sec22 + + + 527.704 + 90 + 0 + OptimaleBL3 - Fuselage Section 23 Positioning + OptimaleBL3 - Fuselage Section 23 Positioning + OptimaleBL3_Fuselage_Sec22 + OptimaleBL3_Fuselage_Sec23 + + + 523.055 + 90 + 0 + OptimaleBL3 - Fuselage Section 24 Positioning + OptimaleBL3 - Fuselage Section 24 Positioning + OptimaleBL3_Fuselage_Sec23 + OptimaleBL3_Fuselage_Sec24 + + + 515.335 + 90 + 0 + OptimaleBL3 - Fuselage Section 25 Positioning + OptimaleBL3 - Fuselage Section 25 Positioning + OptimaleBL3_Fuselage_Sec24 + OptimaleBL3_Fuselage_Sec25 + + + 504.592 + 90 + 0 + OptimaleBL3 - Fuselage Section 26 Positioning + OptimaleBL3 - Fuselage Section 26 Positioning + OptimaleBL3_Fuselage_Sec25 + OptimaleBL3_Fuselage_Sec26 + + + 490.887 + 90 + 0 + OptimaleBL3 - Fuselage Section 27 Positioning + OptimaleBL3 - Fuselage Section 27 Positioning + OptimaleBL3_Fuselage_Sec26 + OptimaleBL3_Fuselage_Sec27 + + + 474.302 + 90 + 0 + OptimaleBL3 - Fuselage Section 28 Positioning + OptimaleBL3 - Fuselage Section 28 Positioning + OptimaleBL3_Fuselage_Sec27 + OptimaleBL3_Fuselage_Sec28 + + + 454.933 + 90 + 0 + OptimaleBL3 - Fuselage Section 29 Positioning + OptimaleBL3 - Fuselage Section 29 Positioning + OptimaleBL3_Fuselage_Sec28 + OptimaleBL3_Fuselage_Sec29 + + + 432.895 + 90 + 0 + OptimaleBL3 - Fuselage Section 30 Positioning + OptimaleBL3 - Fuselage Section 30 Positioning + OptimaleBL3_Fuselage_Sec29 + OptimaleBL3_Fuselage_Sec30 + + + 408.316 + 90 + 0 + OptimaleBL3 - Fuselage Section 31 Positioning + OptimaleBL3 - Fuselage Section 31 Positioning + OptimaleBL3_Fuselage_Sec30 + OptimaleBL3_Fuselage_Sec31 + + + 381.341 + 90 + 0 + OptimaleBL3 - Fuselage Section 32 Positioning + OptimaleBL3 - Fuselage Section 32 Positioning + OptimaleBL3_Fuselage_Sec31 + OptimaleBL3_Fuselage_Sec32 + + + 352.128 + 90 + 0 + OptimaleBL3 - Fuselage Section 33 Positioning + OptimaleBL3 - Fuselage Section 33 Positioning + OptimaleBL3_Fuselage_Sec32 + OptimaleBL3_Fuselage_Sec33 + + + 320.849 + 90 + 0 + OptimaleBL3 - Fuselage Section 34 Positioning + OptimaleBL3 - Fuselage Section 34 Positioning + OptimaleBL3_Fuselage_Sec33 + OptimaleBL3_Fuselage_Sec34 + + + 287.687 + 90 + 0 + OptimaleBL3 - Fuselage Section 35 Positioning + OptimaleBL3 - Fuselage Section 35 Positioning + OptimaleBL3_Fuselage_Sec34 + OptimaleBL3_Fuselage_Sec35 + + + 252.837 + 90 + 0 + OptimaleBL3 - Fuselage Section 36 Positioning + OptimaleBL3 - Fuselage Section 36 Positioning + OptimaleBL3_Fuselage_Sec35 + OptimaleBL3_Fuselage_Sec36 + + + 216.503 + 90 + 0 + OptimaleBL3 - Fuselage Section 37 Positioning + OptimaleBL3 - Fuselage Section 37 Positioning + OptimaleBL3_Fuselage_Sec36 + OptimaleBL3_Fuselage_Sec37 + + + 178.898 + 90 + 0 + OptimaleBL3 - Fuselage Section 38 Positioning + OptimaleBL3 - Fuselage Section 38 Positioning + OptimaleBL3_Fuselage_Sec37 + OptimaleBL3_Fuselage_Sec38 + + + 140.243 + 90 + 0 + OptimaleBL3 - Fuselage Section 39 Positioning + OptimaleBL3 - Fuselage Section 39 Positioning + OptimaleBL3_Fuselage_Sec38 + OptimaleBL3_Fuselage_Sec39 + + + 100.766 + 90 + 0 + OptimaleBL3 - Fuselage Section 40 Positioning + OptimaleBL3 - Fuselage Section 40 Positioning + OptimaleBL3_Fuselage_Sec39 + OptimaleBL3_Fuselage_Sec40 + + + 60.697 + 90 + 0 + OptimaleBL3 - Fuselage Section 41 Positioning + OptimaleBL3 - Fuselage Section 41 Positioning + OptimaleBL3_Fuselage_Sec40 + OptimaleBL3_Fuselage_Sec41 + + + 20.272 + 90 + 0 + OptimaleBL3 - Fuselage Section 42 Positioning + OptimaleBL3 - Fuselage Section 42 Positioning + OptimaleBL3_Fuselage_Sec41 + OptimaleBL3_Fuselage_Sec42 + + + + + Segment from OptimaleBL3 - Fuselage Section 1 Main Element to OptimaleBL3 - Fuselage Section 2 Main Element + Segment from OptimaleBL3 - Fuselage Section 1 Main Element to OptimaleBL3 - Fuselage Section 2 Main Element + OptimaleBL3_Fuselage_Sec1_El1 + OptimaleBL3_Fuselage_Sec2_El1 + + + Segment from OptimaleBL3 - Fuselage Section 2 Main Element to OptimaleBL3 - Fuselage Section 3 Main Element + Segment from OptimaleBL3 - Fuselage Section 2 Main Element to OptimaleBL3 - Fuselage Section 3 Main Element + OptimaleBL3_Fuselage_Sec2_El1 + OptimaleBL3_Fuselage_Sec3_El1 + + + Segment from OptimaleBL3 - Fuselage Section 3 Main Element to OptimaleBL3 - Fuselage Section 4 Main Element + Segment from OptimaleBL3 - Fuselage Section 3 Main Element to OptimaleBL3 - Fuselage Section 4 Main Element + OptimaleBL3_Fuselage_Sec3_El1 + OptimaleBL3_Fuselage_Sec4_El1 + + + Segment from OptimaleBL3 - Fuselage Section 4 Main Element to OptimaleBL3 - Fuselage Section 5 Main Element + Segment from OptimaleBL3 - Fuselage Section 4 Main Element to OptimaleBL3 - Fuselage Section 5 Main Element + OptimaleBL3_Fuselage_Sec4_El1 + OptimaleBL3_Fuselage_Sec5_El1 + + + Segment from OptimaleBL3 - Fuselage Section 5 Main Element to OptimaleBL3 - Fuselage Section 6 Main Element + Segment from OptimaleBL3 - Fuselage Section 5 Main Element to OptimaleBL3 - Fuselage Section 6 Main Element + OptimaleBL3_Fuselage_Sec5_El1 + OptimaleBL3_Fuselage_Sec6_El1 + + + Segment from OptimaleBL3 - Fuselage Section 6 Main Element to OptimaleBL3 - Fuselage Section 7 Main Element + Segment from OptimaleBL3 - Fuselage Section 6 Main Element to OptimaleBL3 - Fuselage Section 7 Main Element + OptimaleBL3_Fuselage_Sec6_El1 + OptimaleBL3_Fuselage_Sec7_El1 + + + Segment from OptimaleBL3 - Fuselage Section 7 Main Element to OptimaleBL3 - Fuselage Section 8 Main Element + Segment from OptimaleBL3 - Fuselage Section 7 Main Element to OptimaleBL3 - Fuselage Section 8 Main Element + OptimaleBL3_Fuselage_Sec7_El1 + OptimaleBL3_Fuselage_Sec8_El1 + + + Segment from OptimaleBL3 - Fuselage Section 8 Main Element to OptimaleBL3 - Fuselage Section 9 Main Element + Segment from OptimaleBL3 - Fuselage Section 8 Main Element to OptimaleBL3 - Fuselage Section 9 Main Element + OptimaleBL3_Fuselage_Sec8_El1 + OptimaleBL3_Fuselage_Sec9_El1 + + + Segment from OptimaleBL3 - Fuselage Section 9 Main Element to OptimaleBL3 - Fuselage Section 10 Main Element + Segment from OptimaleBL3 - Fuselage Section 9 Main Element to OptimaleBL3 - Fuselage Section 10 Main Element + OptimaleBL3_Fuselage_Sec9_El1 + OptimaleBL3_Fuselage_Sec10_El1 + + + Segment from OptimaleBL3 - Fuselage Section 10 Main Element to OptimaleBL3 - Fuselage Section 11 Main Element + Segment from OptimaleBL3 - Fuselage Section 10 Main Element to OptimaleBL3 - Fuselage Section 11 Main Element + OptimaleBL3_Fuselage_Sec10_El1 + OptimaleBL3_Fuselage_Sec11_El1 + + + Segment from OptimaleBL3 - Fuselage Section 11 Main Element to OptimaleBL3 - Fuselage Section 12 Main Element + Segment from OptimaleBL3 - Fuselage Section 11 Main Element to OptimaleBL3 - Fuselage Section 12 Main Element + OptimaleBL3_Fuselage_Sec11_El1 + OptimaleBL3_Fuselage_Sec12_El1 + + + Segment from OptimaleBL3 - Fuselage Section 12 Main Element to OptimaleBL3 - Fuselage Section 13 Main Element + Segment from OptimaleBL3 - Fuselage Section 12 Main Element to OptimaleBL3 - Fuselage Section 13 Main Element + OptimaleBL3_Fuselage_Sec12_El1 + OptimaleBL3_Fuselage_Sec13_El1 + + + Segment from OptimaleBL3 - Fuselage Section 13 Main Element to OptimaleBL3 - Fuselage Section 14 Main Element + Segment from OptimaleBL3 - Fuselage Section 13 Main Element to OptimaleBL3 - Fuselage Section 14 Main Element + OptimaleBL3_Fuselage_Sec13_El1 + OptimaleBL3_Fuselage_Sec14_El1 + + + Segment from OptimaleBL3 - Fuselage Section 14 Main Element to OptimaleBL3 - Fuselage Section 15 Main Element + Segment from OptimaleBL3 - Fuselage Section 14 Main Element to OptimaleBL3 - Fuselage Section 15 Main Element + OptimaleBL3_Fuselage_Sec14_El1 + OptimaleBL3_Fuselage_Sec15_El1 + + + Segment from OptimaleBL3 - Fuselage Section 15 Main Element to OptimaleBL3 - Fuselage Section 16 Main Element + Segment from OptimaleBL3 - Fuselage Section 15 Main Element to OptimaleBL3 - Fuselage Section 16 Main Element + OptimaleBL3_Fuselage_Sec15_El1 + OptimaleBL3_Fuselage_Sec16_El1 + + + Segment from OptimaleBL3 - Fuselage Section 16 Main Element to OptimaleBL3 - Fuselage Section 17 Main Element + Segment from OptimaleBL3 - Fuselage Section 16 Main Element to OptimaleBL3 - Fuselage Section 17 Main Element + OptimaleBL3_Fuselage_Sec16_El1 + OptimaleBL3_Fuselage_Sec17_El1 + + + Segment from OptimaleBL3 - Fuselage Section 17 Main Element to OptimaleBL3 - Fuselage Section 18 Main Element + Segment from OptimaleBL3 - Fuselage Section 17 Main Element to OptimaleBL3 - Fuselage Section 18 Main Element + OptimaleBL3_Fuselage_Sec17_El1 + OptimaleBL3_Fuselage_Sec18_El1 + + + Segment from OptimaleBL3 - Fuselage Section 18 Main Element to OptimaleBL3 - Fuselage Section 19 Main Element + Segment from OptimaleBL3 - Fuselage Section 18 Main Element to OptimaleBL3 - Fuselage Section 19 Main Element + OptimaleBL3_Fuselage_Sec18_El1 + OptimaleBL3_Fuselage_Sec19_El1 + + + Segment from OptimaleBL3 - Fuselage Section 19 Main Element to OptimaleBL3 - Fuselage Section 20 Main Element + Segment from OptimaleBL3 - Fuselage Section 19 Main Element to OptimaleBL3 - Fuselage Section 20 Main Element + OptimaleBL3_Fuselage_Sec19_El1 + OptimaleBL3_Fuselage_Sec20_El1 + + + Segment from OptimaleBL3 - Fuselage Section 20 Main Element to OptimaleBL3 - Fuselage Section 21 Main Element + Segment from OptimaleBL3 - Fuselage Section 20 Main Element to OptimaleBL3 - Fuselage Section 21 Main Element + OptimaleBL3_Fuselage_Sec20_El1 + OptimaleBL3_Fuselage_Sec21_El1 + + + Segment from OptimaleBL3 - Fuselage Section 21 Main Element to OptimaleBL3 - Fuselage Section 22 Main Element + Segment from OptimaleBL3 - Fuselage Section 21 Main Element to OptimaleBL3 - Fuselage Section 22 Main Element + OptimaleBL3_Fuselage_Sec21_El1 + OptimaleBL3_Fuselage_Sec23_El1 + + + Segment from OptimaleBL3 - Fuselage Section 23 Main Element to OptimaleBL3 - Fuselage Section 24 Main Element + Segment from OptimaleBL3 - Fuselage Section 23 Main Element to OptimaleBL3 - Fuselage Section 24 Main Element + OptimaleBL3_Fuselage_Sec23_El1 + OptimaleBL3_Fuselage_Sec24_El1 + + + Segment from OptimaleBL3 - Fuselage Section 24 Main Element to OptimaleBL3 - Fuselage Section 25 Main Element + Segment from OptimaleBL3 - Fuselage Section 24 Main Element to OptimaleBL3 - Fuselage Section 25 Main Element + OptimaleBL3_Fuselage_Sec24_El1 + OptimaleBL3_Fuselage_Sec25_El1 + + + Segment from OptimaleBL3 - Fuselage Section 25 Main Element to OptimaleBL3 - Fuselage Section 26 Main Element + Segment from OptimaleBL3 - Fuselage Section 25 Main Element to OptimaleBL3 - Fuselage Section 26 Main Element + OptimaleBL3_Fuselage_Sec25_El1 + OptimaleBL3_Fuselage_Sec26_El1 + + + Segment from OptimaleBL3 - Fuselage Section 26 Main Element to OptimaleBL3 - Fuselage Section 27 Main Element + Segment from OptimaleBL3 - Fuselage Section 26 Main Element to OptimaleBL3 - Fuselage Section 27 Main Element + OptimaleBL3_Fuselage_Sec26_El1 + OptimaleBL3_Fuselage_Sec27_El1 + + + Segment from OptimaleBL3 - Fuselage Section 27 Main Element to OptimaleBL3 - Fuselage Section 28 Main Element + Segment from OptimaleBL3 - Fuselage Section 27 Main Element to OptimaleBL3 - Fuselage Section 28 Main Element + OptimaleBL3_Fuselage_Sec27_El1 + OptimaleBL3_Fuselage_Sec28_El1 + + + Segment from OptimaleBL3 - Fuselage Section 28 Main Element to OptimaleBL3 - Fuselage Section 29 Main Element + Segment from OptimaleBL3 - Fuselage Section 28 Main Element to OptimaleBL3 - Fuselage Section 29 Main Element + OptimaleBL3_Fuselage_Sec28_El1 + OptimaleBL3_Fuselage_Sec29_El1 + + + Segment from OptimaleBL3 - Fuselage Section 29 Main Element to OptimaleBL3 - Fuselage Section 30 Main Element + Segment from OptimaleBL3 - Fuselage Section 29 Main Element to OptimaleBL3 - Fuselage Section 30 Main Element + OptimaleBL3_Fuselage_Sec29_El1 + OptimaleBL3_Fuselage_Sec30_El1 + + + Segment from OptimaleBL3 - Fuselage Section 30 Main Element to OptimaleBL3 - Fuselage Section 31 Main Element + Segment from OptimaleBL3 - Fuselage Section 30 Main Element to OptimaleBL3 - Fuselage Section 31 Main Element + OptimaleBL3_Fuselage_Sec30_El1 + OptimaleBL3_Fuselage_Sec31_El1 + + + Segment from 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OptimaleBL3_Fuselage_Sec37_El1 + OptimaleBL3_Fuselage_Sec38_El1 + + + Segment from OptimaleBL3 - Fuselage Section 38 Main Element to OptimaleBL3 - Fuselage Section 39 Main Element + Segment from OptimaleBL3 - Fuselage Section 38 Main Element to OptimaleBL3 - Fuselage Section 39 Main Element + OptimaleBL3_Fuselage_Sec38_El1 + OptimaleBL3_Fuselage_Sec39_El1 + + + Segment from OptimaleBL3 - Fuselage Section 39 Main Element to OptimaleBL3 - Fuselage Section 40 Main Element + Segment from OptimaleBL3 - Fuselage Section 39 Main Element to OptimaleBL3 - Fuselage Section 40 Main Element + OptimaleBL3_Fuselage_Sec39_El1 + OptimaleBL3_Fuselage_Sec40_El1 + + + Segment from OptimaleBL3 - Fuselage Section 40 Main Element to OptimaleBL3 - Fuselage Section 41 Main Element + Segment from OptimaleBL3 - Fuselage Section 40 Main Element to OptimaleBL3 - Fuselage Section 41 Main Element + OptimaleBL3_Fuselage_Sec40_El1 + OptimaleBL3_Fuselage_Sec41_El1 + + + Segment from OptimaleBL3 - Fuselage Section 41 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;-0.049452 ;-0.045919 ;-0.041032 ;-0.034397 ;-0.030137 + ;-0.024954 ;-0.018011 ;-0.013038 ;-0.010317 ;-0.008572 ;0.000000 ;0.008572 ;0.010317 + ;0.013038 ;0.018011 ;0.024954 ;0.030137 ;0.034397 ;0.041032 ;0.045919 ;0.049452 + ;0.051842 ;0.053150 ;0.053253 ;0.051949 ;0.049506 ;0.046177 ;0.042148 ;0.037536 + ;0.032470 ;0.027121 ;0.021714 ;0.016321 ;0.010942 ;0.005576 ;0.000224 + + + + + + + + + + False + Euler + False + 10.0 + + 5.0 + + 3.0 + 0.003 + + + 10.0 + 0.007 + + 0.23 + 0.23 + + 2.0 + 0.9 + 4.0 + False + False + 20 + 3.0 + 100.0 + 1.2 + 1.4 + 40.0 + False + 20.0 + 20.0 + + 5.0 + + + + \ No newline at end of file diff --git a/tests/docker/Centos/Dockerfile b/tests/docker/Centos/Dockerfile index 4c664e6e3..ca6c8d7f9 100644 --- a/tests/docker/Centos/Dockerfile +++ b/tests/docker/Centos/Dockerfile @@ -19,8 +19,10 @@ RUN source ~/.bashrc RUN conda update -n base -c defaults conda WORKDIR /CEASIOMpy/CEASIOMpy/installation/CentOS/ +RUN chmod +x install_*.sh RUN ./install_ceasiompy.sh RUN ./install_ceasiompy.sh +RUN ./install_pyavl.sh RUN ./install_pytornado.sh RUN ./install_sumo.sh RUN ./install_su2.sh diff --git a/tests/test_integration_tests.py b/tests/test_integration_tests.py index 87173559e..d2b74c6f7 100644 --- a/tests/test_integration_tests.py +++ b/tests/test_integration_tests.py @@ -112,6 +112,17 @@ def test_integration_4(): assert workflow_ends() +@pytest.mark.slow +@pytest.mark.skipif(not shutil.which("avl"), reason="avl not installed") +def test_integration_5(): + modules_to_run = ["PyAVL", "SaveAeroCoefficients"] + + with change_working_dir(WORKFLOW_TEST_DIR): + run_modules_list([str(CPACS_IN_PATH), *modules_to_run]) + + assert workflow_ends() + + # ================================================================================================= # MAIN # =================================================================================================