Improvement of the mesh generation and control pt. 1

ceasiompy/CPACS2GMSH/__specs__.py

@@ -5,6 +5,8 @@
     GMSH_EXHAUST_PERCENT_XPATH,
     GMSH_EXPORT_PROP_XPATH,
     GMSH_FARFIELD_FACTOR_XPATH,
+    GMSH_N_POWER_FACTOR_XPATH,
+    GMSH_N_POWER_FIELD_XPATH,
     GMSH_INTAKE_PERCENT_XPATH,
     GMSH_MESH_SIZE_FARFIELD_XPATH,
     GMSH_MESH_SIZE_FUSELAGE_XPATH,
@@ -16,6 +18,8 @@
     GMSH_REFINE_FACTOR_XPATH,
     GMSH_SYMMETRY_XPATH,
     SU2MESH_XPATH,
+    GMSH_MESH_SIZE_FACTOR_FUSELAGE_XPATH,
+    GMSH_MESH_SIZE_FACTOR_WINGS_XPATH,
 )
 from ceasiompy.utils.moduleinterfaces import CPACSInOut
 
@@ -84,38 +88,39 @@
 )
 
 cpacs_inout.add_input(
-    var_name="farfield_mesh_size",
+    var_name="farfield_mesh_size_factor",
     var_type=float,
-    default_value=25,
-    unit="[m]",
-    descr="Value assigned for the farfield surface mesh size",
+    default_value=10,
+    unit="[-]",
+    descr="""Factor proportional to the biggest cell on the plane
+            to obtain cell size on the farfield""",
     xpath=GMSH_MESH_SIZE_FARFIELD_XPATH,
     gui=True,
-    gui_name="Farfield",
+    gui_name="Farfield mesh size factor",
     gui_group="Mesh size",
 )
 
 cpacs_inout.add_input(
-    var_name="fuselage_mesh_size",
+    var_name="fuselage_mesh_size_factor",
     var_type=float,
-    default_value=0.4,
-    unit="[m]",
-    descr="Value assigned for the fuselage surfaces mesh size",
-    xpath=GMSH_MESH_SIZE_FUSELAGE_XPATH,
+    default_value=1,
+    unit="[-]",
+    descr="Factor proportional to fuselage radius of curvature to obtain cell size on it",
+    xpath=GMSH_MESH_SIZE_FACTOR_FUSELAGE_XPATH,
     gui=True,
-    gui_name="Fuselage",
+    gui_name="Fuselage mesh size factor",
     gui_group="Mesh size",
 )
 
 cpacs_inout.add_input(
-    var_name="wing_mesh_size",
+    var_name="wing_mesh_size_factor",
     var_type=float,
-    default_value=0.23,
-    unit="[m]",
-    descr="Value assigned for the wings surfaces mesh size",
-    xpath=GMSH_MESH_SIZE_WINGS_XPATH,
+    default_value=1.5,
+    unit="[-]",
+    descr="Factor proportional to wing radius of curvature to obtain cell size on it",
+    xpath=GMSH_MESH_SIZE_FACTOR_WINGS_XPATH,
     gui=True,
-    gui_name="Wings",
+    gui_name="Wings mesh size factor",
     gui_group="Mesh size",
 )
 
@@ -130,6 +135,7 @@
     gui_name="Engines",
     gui_group="Mesh size",
 )
+
 cpacs_inout.add_input(
     var_name="propeller_mesh_size",
     var_type=float,
@@ -142,10 +148,34 @@
     gui_group="Mesh size",
 )
 
+cpacs_inout.add_input(
+    var_name="n_power_factor",
+    var_type=float,
+    default_value=2,
+    unit="1",
+    descr="Value that changes the number of cells near the aircraft parts",
+    xpath=GMSH_N_POWER_FACTOR_XPATH,
+    gui=True,
+    gui_name="n power factor",
+    gui_group="Advanced mesh parameters",
+)
+
+cpacs_inout.add_input(
+    var_name="n_power_field",
+    var_type=float,
+    default_value=0.9,
+    unit="1",
+    descr="Value that changes the measure of fist cells near aircraft parts",
+    xpath=GMSH_N_POWER_FIELD_XPATH,
+    gui=True,
+    gui_name="n power field",
+    gui_group="Advanced mesh parameters",
+)
+
 cpacs_inout.add_input(
     var_name="refine_factor",
     var_type=float,
-    default_value=7.0,
+    default_value=2.0,
     unit="1",
     descr="Refinement factor of wing leading/trailing edge mesh",
     xpath=GMSH_REFINE_FACTOR_XPATH,
@@ -168,7 +198,7 @@
 cpacs_inout.add_input(
     var_name="auto_refine",
     var_type=bool,
-    default_value=True,
+    default_value=False,
     unit="1",
     descr="Automatically refine the mesh on surfaces that are small compare to the chosen mesh"
     "size, this option increase the mesh generation time",

ceasiompy/CPACS2GMSH/cpacs2gmsh.py

@@ -33,10 +33,12 @@
     GMSH_AUTO_REFINE_XPATH,
     GMSH_EXHAUST_PERCENT_XPATH,
     GMSH_FARFIELD_FACTOR_XPATH,
+    GMSH_N_POWER_FACTOR_XPATH,
+    GMSH_N_POWER_FIELD_XPATH,
     GMSH_INTAKE_PERCENT_XPATH,
     GMSH_MESH_SIZE_FARFIELD_XPATH,
-    GMSH_MESH_SIZE_FUSELAGE_XPATH,
-    GMSH_MESH_SIZE_WINGS_XPATH,
+    GMSH_MESH_SIZE_FACTOR_FUSELAGE_XPATH,
+    GMSH_MESH_SIZE_FACTOR_WINGS_XPATH,
     GMSH_MESH_SIZE_ENGINES_XPATH,
     GMSH_MESH_SIZE_PROPELLERS_XPATH,
     GMSH_OPEN_GUI_XPATH,
@@ -65,7 +67,6 @@
 
 
 def cpacs2gmsh(cpacs_path, cpacs_out_path):
-
     # Get option from the CPACS file
     cpacs = CPACS(cpacs_path)
 
@@ -78,9 +79,15 @@ def cpacs2gmsh(cpacs_path, cpacs_out_path):
     open_gmsh = get_value_or_default(cpacs.tixi, GMSH_OPEN_GUI_XPATH, False)
     farfield_factor = get_value_or_default(cpacs.tixi, GMSH_FARFIELD_FACTOR_XPATH, 6)
     symmetry = get_value_or_default(cpacs.tixi, GMSH_SYMMETRY_XPATH, False)
-    mesh_size_farfield = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_FARFIELD_XPATH, 25)
-    mesh_size_fuselage = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_FUSELAGE_XPATH, 0.4)
-    mesh_size_wings = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_WINGS_XPATH, 0.23)
+    farfield_size_factor = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_FARFIELD_XPATH, 17)
+    n_power_factor = get_value_or_default(cpacs.tixi, GMSH_N_POWER_FACTOR_XPATH, 2)
+    n_power_field = get_value_or_default(cpacs.tixi, GMSH_N_POWER_FIELD_XPATH, 0.9)
+    fuselage_mesh_size_factor = get_value_or_default(
+        cpacs.tixi,
+        GMSH_MESH_SIZE_FACTOR_FUSELAGE_XPATH,
+        1,
+    )
+    wing_mesh_size_factor = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_FACTOR_WINGS_XPATH, 1)
     mesh_size_engines = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_ENGINES_XPATH, 0.23)
     mesh_size_propellers = get_value_or_default(cpacs.tixi, GMSH_MESH_SIZE_PROPELLERS_XPATH, 0.23)
     refine_factor = get_value_or_default(cpacs.tixi, GMSH_REFINE_FACTOR_XPATH, 7.0)
@@ -93,14 +100,17 @@ def cpacs2gmsh(cpacs_path, cpacs_out_path):
     export_brep(cpacs, brep_dir, (intake_percent, exhaust_percent))
     mesh_path, _ = generate_gmsh(
         cpacs,
+        cpacs_path,
         brep_dir,
         results_dir,
         open_gmsh=open_gmsh,
         farfield_factor=farfield_factor,
         symmetry=symmetry,
-        mesh_size_farfield=mesh_size_farfield,
-        mesh_size_fuselage=mesh_size_fuselage,
-        mesh_size_wings=mesh_size_wings,
+        farfield_size_factor=farfield_size_factor,
+        n_power_factor=n_power_factor,
+        n_power_field=n_power_field,
+        fuselage_mesh_size_factor=fuselage_mesh_size_factor,
+        wing_mesh_size_factor=wing_mesh_size_factor,
         mesh_size_engines=mesh_size_engines,
         mesh_size_propellers=mesh_size_propellers,
         refine_factor=refine_factor,
@@ -124,7 +134,6 @@ def cpacs2gmsh(cpacs_path, cpacs_out_path):
 
 
 def main(cpacs_path, cpacs_out_path):
-
     log.info("----- Start of " + MODULE_NAME + " -----")
 
     check_cpacs_input_requirements(cpacs_path)
@@ -135,7 +144,6 @@ def main(cpacs_path, cpacs_out_path):
 
 
 if __name__ == "__main__":
-
     cpacs_path = get_toolinput_file_path(MODULE_NAME)
     cpacs_out_path = get_tooloutput_file_path(MODULE_NAME)
 

ceasiompy/CPACS2GMSH/func/advancemeshing.py

@@ -12,8 +12,7 @@
 
 TODO:
 
-    -Add a parameter to let the user tune the powerlaw governing the mesh
-    in the fluid domaine and the powerlaw for the wing surface mesh
+    -Add a parameter to let the user tune the powerlaw for the wing surface mesh
 
 """
 
@@ -253,14 +252,12 @@ def refine_wing_section(
 
     # For each wing section get the mean chord and le/te lines
     for wing_section in wing_part.wing_sections:
-
         chord_mean = wing_section["mean_chord"]
         x_chord = chord_mean * chord_percent
         lines_to_refine = wing_section["lines_tags"]
 
         # If the wing is truncated:
         if len(lines_to_refine) == 3:
-
             # Find the trailing edge thickness
             x1, y1, z1 = gmsh.model.occ.getCenterOfMass(1, lines_to_refine[0])
             x2, y2, z2 = gmsh.model.occ.getCenterOfMass(1, lines_to_refine[1])
@@ -274,7 +271,6 @@ def refine_wing_section(
 
             # Overwrite the trailing edge refinement
             if (mesh_size_wings / te_thickness > refine) and refine_truncated:
-
                 refine = mesh_size_wings / te_thickness
 
         # 1 : Math eval field
@@ -331,7 +327,8 @@ def set_domain_mesh(
     mesh_size_farfield,
     aircraft_charact_length,
     final_domain_volume_tag,
-    n_power=1.5,
+    n_power_factor,
+    n_power_field,
 ):
     """
     Function to define the domain mesh between the farfield and the aircraft
@@ -375,7 +372,6 @@ def set_domain_mesh(
     log.info("Set mesh refinement of fluid domain")
 
     for part in aircraft_parts:
-
         # 1 : Math eval field between the part surface and the farfield
 
         mesh_fields = distance_field(mesh_fields, 2, part.surfaces_tags)
@@ -388,7 +384,7 @@ def set_domain_mesh(
             mesh_fields["nbfields"],
             "F",
             f"{part.mesh_size} + ({mesh_size_farfield} - {part.mesh_size})*"
-            f"(F{distance_field_tag}/{aircraft_charact_length})^{n_power}",
+            f"(F{distance_field_tag}/{aircraft_charact_length})^{n_power_factor}",
         )
         mesh_fields = restrict_fields(mesh_fields, 3, final_domain_volume_tag)
 
@@ -399,7 +395,9 @@ def set_domain_mesh(
         gmsh.model.mesh.field.add("Threshold", mesh_fields["nbfields"])
         gmsh.model.mesh.field.setNumber(mesh_fields["nbfields"], "InField", distance_field_tag)
         gmsh.model.mesh.field.setNumber(mesh_fields["nbfields"], "SizeMax", part.mesh_size)
-        gmsh.model.mesh.field.setNumber(mesh_fields["nbfields"], "SizeMin", part.mesh_size * 0.9)
+        gmsh.model.mesh.field.setNumber(
+            mesh_fields["nbfields"], "SizeMin", part.mesh_size * n_power_field
+        )
 
         mesh_fields = restrict_fields(mesh_fields, 2, part.surfaces_tags)
 
@@ -519,5 +517,4 @@ def refine_small_surfaces(
 # =================================================================================================
 
 if __name__ == "__main__":
-
     print("Nothing to execute!")