Laminar Viscous Solver

This code is a part of final project of Continuum Mechanics II, in Aerospace Engineering ITB

Contributor:

• Ghifari Adam F
• Faber Yosua O
• Hanief Adnadi

This code was written in Python 3.6

Dependencies: numpy, matplotlib, copy

How to use

1. Place all files in one folder: a. main.py b. calc_gamma.m c. dataimport.m d. geometrical_param.m e. gridgen_fcn.py f. dom_velo.py g. 2410.txt

2. The .txt file (Airfoil coordinates) follows selig format (Start from trailing edge and goes CCW)

3. Run main.py on the console

4. Input known values. Example:

   Freestream velocity: 10 m/s Angle of Attack: 0 deg Airfoil file: 2410.txt