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Numerical Analysis of Hypersonic Shock-Shock Interaction Using AUSMPW+ Scheme and Gas Reaction Models

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Authors
Lee, Joon Ho; Kim, Chongam; Rho, Oh-Hyun
Issue Date
2000-04
Publisher
The Korean Society for Aeronautical & Space Sciences
Citation
KSAS Interntional Journal Vol.1 No.1, pp. 21-28
Keywords
공학hypersonic flowshock-shock interactionAUSMPW+ schemegas reaction model
Abstract
The flowfield of hypersonic shock- shock interaction has been simulated using a
two- dimensional Navier-Stokes code based on AUSMPW+ scheme. AUSMPW+ scheme
is a new hybrid flux splitting scheme, which is improved by introducing pressure- based
weight functions to eliminate the typical drawbacks of AUSM - type schemes, such as
non- monotone pressure solutions. To study the real gas effects, three different gas models
are taken into account in the present paper: perfect gas, equilibrium flow and nonequilibrium
flow. It has been investigated how each gas model influences on the peak surface loading,
such as wall pressure and wall heat transfer, and unsteady structure of flowfield in the
region of shock- shock interaction. With the results, the value of peak pressure is not
sensitive to the real gas effects nor to the wall catalyticity. However, the value of peak
heat transfer rates is affected by the real gas effects and the wall catalyticity. Also,
the structure of the flowfield changes drastically in the presence of real gas effects.
Language
English
URI
http://hdl.handle.net/10371/82293
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Journal Papers (저널논문_기계항공공학부)
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