CFD-Wiki talk:Contribute something today
now i am writing a CFD code to compute the shock wave impinge into supersonic boundary layer,which will cause separation. first i use BL turbulence model. up to now,i can obtain some numerical results but how to prove the results are right?i can't find the data,and who can help me and provide the data to validation.
the shock angle is 34.5o Ma=2 Re=2.96E+5 gama=1.4
- I'm not sure if I understand what the question was in relation to CFD-Wiki. Note that this talk page is only for the CFD-Wiki page called "Contribute something today". --Jola 02:48, 13 June 2007 (MDT)