Flow phenomena and separation over highly swept delta wings with trailing-edge flaps at Mach 6
Author:
Affiliation:
1. NASA, LANGLEY RESEARCH CENTER, HAMPTON, VA.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1968-97
Reference29 articles.
1. from Mach 3 to 7." AFQC-TR-66-19, January 1967. flaa-induced swaration of transitional and turbu
2. Earnshaw, P. B., and Lawford, J. A. "Law-Speed Wind-Tunnel Experiments on a Series of Sharp-Edged Delta Wings,'' R. & M. No. 3424, March 1964.
Cited by 3 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. Aerodynamics of delta wings with flaps at hypersonic speeds;The Aeronautical Journal;2002-06
2. Experimental investigation of hypersonic flow over a wing-body combination;International Aerospace Planes and Hypersonics Technologies;1995-04-03
3. Results of an experimental and numerical study of the aerodynamic heating of the undersurface of delta wings with sharp leading edges at mach numbers M?=6.1 and 8;Fluid Dynamics;1992
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