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Perfect gas navier-stokes solutions hypersonic boundary layer and compression corner flows
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Date
2005
Author
Aziz, Şaduman
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The purpose of this thesis is to perform numerical solutions of hypersonic, high temperature, perfect gas flows over various geometries. Three dimensional, thin layer, compressible, Navier-Stokes equations are solved. An upwind finite difference approach with Lower Upper-Alternating Direction Implicit (LU-ADI) decomposition is used. Solutions of laminar, hypersonic, high temperature, perfect gas flows over flat plate and compression corners (qw=5°, 10°, 14°, 15°, 16°, 18° and 24°) with eight different free-stream and wall conditions are presented and discussed. During the analysis, air viscosity is calculated from the Sutherland formula up to 1000°K, for the temperature range between 1000 ðK and 5000 ðK a curve fit to the estimations of Svehla is applied. The effects of Tw/T0 on heat transfer rates, surface pressure distributions and boundary layer characteristics are studied. The effects of corner angle (?w) on strong shock wave/boundary layer interactions with extended separated regions are investigated. The obtained results are compared with the available experimental data, computational results, and theory.
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Science.
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http://etd.lib.metu.edu.tr/upload/12606661/index.pdf
https://hdl.handle.net/11511/15826
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Graduate School of Natural and Applied Sciences, Thesis
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Ş. Aziz, “Perfect gas navier-stokes solutions hypersonic boundary layer and compression corner flows,” Ph.D. - Doctoral Program, Middle East Technical University, 2005.
