Coupled Analytical-Numerical Procedure to Solve the Double Wedge Spiked Supersonic Intake Flow Field
Designers of the aero engines are in quest of maintaining the pressure as high as possible at the face of the compressor, with air velocity not higher than 0.8 Mach. Reduction of the flow from supersonic to such speed is combined with pressure reduction. This paper presents results from coupled tech...
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Scientific.net
2012
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| 在線閱讀: | http://eprints.utp.edu.my/8913/1/AMM.225.67 http://www.scientific.net/AMM.225.67# http://eprints.utp.edu.my/8913/ |
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