Unsteady simulation of hypersonic flow around a heat flux probe in ground testing conditions

Unsteady simulation of hypersonic flow around a heat flux probe in ground testing conditions

•An inverse method for validating the rebuilding process of the free stream conditions in hypersonic facility is proposed.•Unsteady time accurate Naiver-Stokes simulation around the heat flux probe was performed.•Fay-Riddell approximation remains valid for quasi-steady hypersonic flows. In order to...

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Bibliographic Details
Published in:International journal of heat and mass transfer Vol. 113; pp. 889 - 897
Main Authors: Bensassi, K., Lani, A., Rambaud, P.
Format: Journal Article
Language:English
Published: Oxford Elsevier Ltd 01-10-2017
Elsevier BV
Subjects:
Aerodynamics
Axisymmetric flow
CFD
Computer simulation
Enthalpy
Fluid dynamics
Ground tests
Heat flux
Heat transfer
Hypersonic flow
Hypersonic flows
Numerical analysis
Stagnation pressure
Studies
Time integration
Unsteady
Wind tunnel testing
Windows (intervals)
CFD
Hypersonic flows
Wind tunnel testing
Unsteady
Heat flux
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Summary:•An inverse method for validating the rebuilding process of the free stream conditions in hypersonic facility is proposed.•Unsteady time accurate Naiver-Stokes simulation around the heat flux probe was performed.•Fay-Riddell approximation remains valid for quasi-steady hypersonic flows. In order to investigate the accuracy of the rebuilding code for the free stream conditions and the total enthalpy in the Longshot Hypersonic facility at the von Karman Institute (VKI), a series of unsteady CFD simulations of axisymmetric hypersonic flow over a heat flux probe have been performed. The free stream and the total conditions provided by experiments as a function of time were used as unsteady inlet boundary conditions for those simulations. The full duration (15ms) of the test window is simulated by means of an implicit time accurate finite volume solver. The numerical method and the time integration procedure used during this investigation are described. The numerical results are within 6% of the experimental data for both the stagnation pressure and the heat flux at the reference test time conditions.
ISSN:0017-9310
1879-2189
DOI:10.1016/j.ijheatmasstransfer.2017.05.096