Shock wave over the wing in transonic flow
I am running the inviscid transonic flow over ONERA M6 wing (density-based case) but I am not getting the shock-wave over the wing. I am running at M=0.84 and AoA=3.06. The questions that I want to confirm are:
1. Can we get shock wave with first order scheme or i need to use second order scheme.
2. In solution methods do I need to choose Implicit or Explicit (I am choosen implicit)
3. Which smoothing shoukd i use AUSM or Roe
I am sure that my mesh is fine.
Any help will be greatly appreciated.
Thanks in advance
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