I would like to plot a velocity field over a flate plate airfoil inclined at an angle of attack alpha (alpha = 5°).
The velocity is defined by the Mach numbber being 5. The air is considerate as an ideal gas, and at sea level.
The dimension of the airfoil are (2D):
chord length = 1m
height = 0.05m
I also would like to have a CFD solution
Tell me if there are missing informations.
Thank you in advanceI would like to plot a velocity field over a flate plate airfoil inclined at an angle of attack alpha (alpha = 5°).
The velocity is defined by the Mach numbber being 5. The air is considerate as an ideal gas, and at sea level.
The dimension of the airfoil are (2D):
chord length = 1m
height = 0.05m
I also would like to have a CFD solution
Tell me if there are missing informations.
Thank you in advance I would like to plot a velocity field over a flate plate airfoil inclined at an angle of attack alpha (alpha = 5°).
The velocity is defined by the Mach numbber being 5. The air is considerate as an ideal gas, and at sea level.
The dimension of the airfoil are (2D):
chord length = 1m
height = 0.05m
I also would like to have a CFD solution
Tell me if there are missing informations.
Thank you in advance homework, compressible flow, cfd MATLAB Answers — New Questions

​