These include hypersonic re-entry flows where bow shocks or detached shocks are formed.
https://www.researchgate.net/publication/2648095_Validation_Of_The_Spalart-Allmaras_Turbulence_Model_For_Application_In_Hypersonic_Flows
follow the above link which talks about validation of S-A model for hyper-sonic flow.
Thanks for the answer.
Are the equations of Fay and Riddell embedded in Fluent or do they have to be imported using a UDF?
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As usually the trend is a Courant number (CFL no) can only be used for a Transient( Unsteady) flow condition. Thank you in Advance.
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Typically at Hypersonic Free Stream Mach numbers and to capture the flow separation and reattachment in the afterbody flow of a re-entry capsule
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I am not clear whether to use a Pressure Based Solver or a Density Based Solver. Thank You in Advance
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Generally after the calculation has been run and during post processing of results in either FLUENT or CFD-POST.
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Typically a 3D adaptive grid for simulating the afterbody flow of a reentry capsule.
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I would like to know the boundary conditions for simulating the above .
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Typically Hypersonic Afterbody flows involving blunt body re-entry vehicles(spacecraft) with an angle of attack and flow separation taking place in the afterbody flow.
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