Analysis of whitcomb in ansys fluent
Hello everyone,
I am a student trying to do my project on 2D analysis of airfoil, I have selected a supercritical airfoil I.e whitcomb super integral airfoil (http://airfoiltools.com/airfoil/deta...il=whitcomb-il ) I have done my meshing in GAMBIT and imported it in ansys fluent in mesh format Which is a C type grid Chord length=1.436 metre Velocity =254m/s Mach no= 0.85 Density=0.389 Viscosity=14.4e-6 Using a pressure based solver And with Spalart Allmaras equation When I am initialising and Running the calculations my continuity equation is diverging. I have tried changing my mesh but it still converges. I don’t know where I am going wrong. Can you please help me with my problem Sorry and thanks for you help |
Density
If M = 0.85, why is density constant? For M >= 0.3, flow is always compressible, therefore, density should be based on ideal or real gas.
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