Computation of 3D asymmetric crossing shock wave/turbulent boundary layer interaction using a full Reynolds stress equation turbulence model

GeCheng Zha, Doyle Knight

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

The three dimensional crossing shock waveturbulent boundary layer interaction caused by an asymmetric 70 x 110 double fin was calculated by solving the Reynolds averaged Navier-Stokes equations with a full Reynolds Stress Equation turbulence model. An implicit approximate factorization method is used for the temporal integration. Roe’s scheme is used for evaluation of the convective terms of the mean flow and Reynolds stress equations with a third order MUSCL-type differencing. The computed surface pressure is in good agreement with the experiment. The computed heat transfer coefficient shows a modest improvement compared with the previous results obtained using the k – ε model with Chien's low Reynolds number correction. Both computations of the heat transfer display significant deviations form the experiment. The tests of the grid refinement, different upstream boundary layer profiles and different isothermal wall temperature axe also presented.

Original languageEnglish (US)
Title of host publication34th Aerospace Sciences Meeting and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9780000000002
StatePublished - 1996
Externally publishedYes
Event34th Aerospace Sciences Meeting and Exhibit, 1996 - Reno, United States
Duration: Jan 15 1996Jan 18 1996

Other

Other34th Aerospace Sciences Meeting and Exhibit, 1996
CountryUnited States
CityReno
Period1/15/961/18/96

Fingerprint

turbulent boundary layer
Reynolds stress
turbulence models
shock wave
Turbulence models
Shock waves
heat transfer
shock waves
boundary layers
Boundary layers
boundary layer
turbulence
wall temperature
Navier-Stokes equations
low Reynolds number
fins
surface pressure
heat transfer coefficients
Factorization
factorization

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Zha, G., & Knight, D. (1996). Computation of 3D asymmetric crossing shock wave/turbulent boundary layer interaction using a full Reynolds stress equation turbulence model. In 34th Aerospace Sciences Meeting and Exhibit American Institute of Aeronautics and Astronautics Inc, AIAA.

Computation of 3D asymmetric crossing shock wave/turbulent boundary layer interaction using a full Reynolds stress equation turbulence model. / Zha, GeCheng; Knight, Doyle.

34th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1996.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Zha, G & Knight, D 1996, Computation of 3D asymmetric crossing shock wave/turbulent boundary layer interaction using a full Reynolds stress equation turbulence model. in 34th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 34th Aerospace Sciences Meeting and Exhibit, 1996, Reno, United States, 1/15/96.
Zha G, Knight D. Computation of 3D asymmetric crossing shock wave/turbulent boundary layer interaction using a full Reynolds stress equation turbulence model. In 34th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA. 1996
Zha, GeCheng ; Knight, Doyle. / Computation of 3D asymmetric crossing shock wave/turbulent boundary layer interaction using a full Reynolds stress equation turbulence model. 34th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1996.
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