How does one simulate a Normal Shock in ANSYS-Fluent ?

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Does ANSYS-Fluent solve the Fay and Riddell equations for calculating Stagnation Heat flux in Hypersonic flows over blunt bodies?

Are the equations of Fay and Riddell embedded in Fluent or do they have to be imported using a UDF?

01 February 2018 7,926 3 View

In Fluent, For a density based solver for steady flow, Is it sensible to have an option for Courant number (CFL no.)?

As usually the trend is a Courant number (CFL no) can only be used for a Transient( Unsteady) flow condition. Thank you in Advance.

01 February 2018 2,041 6 View

Can Detached Eddy Simulation (DES) be used to accurately simulate flow separation in Reentry Capsule Afterbody flows?

Typically at Hypersonic Free Stream Mach numbers and to capture the flow separation and reattachment in the afterbody flow of a re-entry capsule

09 October 2017 818 3 View

Which Solver does one use to simulate flow around a body at Mach 1 in ANSYS -FLUENT?

I am not clear whether to use a Pressure Based Solver or a Density Based Solver. Thank You in Advance

09 October 2017 2,798 18 View

How does one calculate or measure Shock Angle (beta) in ANSYS-FLUENT ?

Generally after the calculation has been run and during post processing of results in either FLUENT or CFD-POST.

08 September 2017 2,417 3 View

How does one make a 3D adaptive grid in ANSYS-FLUENT Meshing console?

Typically a 3D adaptive grid for simulating the afterbody flow of a reentry capsule.

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Which turbulence model is most preferred for modelling Hypersonic Afterbody flows ?

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04 May 2017 10,121 4 View

Can The Spalart–Allmaras viscous model be accurately used in simulating Hypersonic flows(External) in FLUENT?

These include hypersonic re-entry flows where bow shocks or detached shocks are formed.

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Mohammad Zandsalimy

You can use this link. This is a comprehensive step by step explanation, just follow the steps and you got yourself a solution to the compressible flow inside a nozzle. Then change the back pressure to a higher value and see a normal shock inside the nozzle.

Cheers

https://confluence.cornell.edu/display/SIMULATION/FLUENT+-+Compressible+Flow+in+a+Nozzle-+Problem+Specification

Giridharan .D

Instead of RANS equation you can use favre averaged navier stroke equation for supersonic flow. This will give better result for getting normal shockwave.