Hypersonic flowfield over highly swept delta wings with various types of separation is investigated; heat-transfer rates, pressure distributions, and flow-visualization techniques were used to examine flow over large angle-of-attack range; where boundary-layer type differs across span prior to separation, complex and unusual flow phenomena develop; separated flow is found to form coiled vortices in manner similar to that found at subsonic speeds but with several significant differences. (27745)
Flow phenomena and separation over delta wings with trailing-edge flaps at Mach 6
AIAA J
AIAA Journal ; 6 , n 12
1968
8 pages
Aufsatz (Zeitschrift)
Englisch
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