CFD-Wiki talk:Contribute something today

From CFD-Wiki

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