DAFoam for optimization in supersonic flight conditions

[usmanshahid90]

Can we use transonic dafoam for supersonic conditions? If yes, then what are the necessary changes and if not then how to do optimization in supersonic flight conditons?

[friedenhe]

DARhoSimpleCFoam did run for supersonic flow (M=1.2; see the following figure), but we have not verified the flow solutions or done any optimization for supersonic flow with DAFoam. It may work if the Mach number is a bit higher than one. Here is a case if you are interested. To try this case, unzip NACA0012_Supersonic.zip and run python runScript.py. Note that we have to use a good initial field, which was generated by using the upwind scheme. If you use a uniform flow field as the initial condition, the flow will blow up.

NACA0012_Supersonic.zip

[usmanshahid90]

Thank you very much for your reply. I will look into it and will update you accordingly.

[15175829310]

Have you ever done flow field inversion from 0.7 to 0.8 Mach? I am currently using an airfoil to do this work, but the gradient is not calculated.

[friedenhe]

What do you mean by "the gradient is not calculated"?