NCTAM papers, National Congress of Theoretical and Applied Mechanics, Japan
53rd NCTAM papers, National Congress of Theoretical and Applied Mechanics, Japan
Session ID : 1E2
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Numerical Investigation on the Effects of Mach Number and Angle-of -Attack on Leeward Flowfields of Delta Wing at Supersonic Speeds
*Daigo SATO
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Abstract
A series of computation of high angle-of-attack supersonic flows around a sharp-edged delta wing at various flow conditions are conducted using AUSM-DV scheme with 3rd-order MUSCL approach to investigate the effects of freestream Mach Number and angles-of-attack on the leeward side flowfields.
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© 2004 Committee for Mechanics and Structure,Science Council
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