Hi
i want to simulate an airfoil in high mach flow .
i am using high mach number flow module k-epsilon method .also adaptive mesh method employed to finer meshing near shock wave region .
for the special case of airfoil, simulation for all velocity converged(even for higher than 10 mach number flow) and result are acceptable .but when i change slightly dimension of the airfoil ,simulation cannot be converged,even in very low mach number(nearly 2 mach ). I am really confused.nearly two month i am working on this simulation but i can not identify the problem .
to solve the problem please help me.
best regard
i want to simulate an airfoil in high mach flow .
i am using high mach number flow module k-epsilon method .also adaptive mesh method employed to finer meshing near shock wave region .
for the special case of airfoil, simulation for all velocity converged(even for higher than 10 mach number flow) and result are acceptable .but when i change slightly dimension of the airfoil ,simulation cannot be converged,even in very low mach number(nearly 2 mach ). I am really confused.nearly two month i am working on this simulation but i can not identify the problem .
to solve the problem please help me.
best regard