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Applications of an adaptive unstructured solution algorithm to the analysis of high speed flowsAn upwind cell-centered scheme for the solution of steady laminar viscous high-speed flows is implemented on unstructured two-dimensional meshes. The first-order implementation employs Roe's (1981) approximate Riemann solver, and a higher-order extension is produced by using linear reconstruction with limiting. The procedure is applied to the solution of inviscid subsonic flow over an airfoil, inviscid supersonic flow past a cylinder, and viscous hypersonic flow past a double ellipse. A detailed study is then made of a hypersonic laminar viscous flow on a 24-deg compression corner. It is shown that good agreement is achieved with previous predictions using finite-difference and finite-volume schemes. However, these predictions do not agree with experimental observations. With refinement of the structured grid at the leading edge, good agreement with experimental observations for the distributions of wall pressure, heating rate and skin friction is obtained.
Document ID
19900035158
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Thareja, R. R.
(Imperial Coll. of Science and Technology London, United Kingdom)
Prabhu, R. K.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Morgan, K.
(Imperial Coll. of Science and Technology London, United Kingdom)
Peraire, J.
(Imperial Coll. of Science and Technology London, United Kingdom)
Peiro, J.
(Imperial College of Science, Technology, and Medicine London, United Kingdom)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 90-0395
Accession Number
90A22213
Funding Number(s)
CONTRACT_GRANT: NAS1-18000
CONTRACT_GRANT: NAS1-19000
CONTRACT_GRANT: NAGW-1809
Distribution Limits
Public
Copyright
Other

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