Tests made to determine effect of conical wing camber on aerodynamic characteristics of wing body combination having 3% thick wing, at Mach 0.80 to 1.05 and angles of attack from -- 4 to 14°; appendix on influence of leading edge suction and span load efficiency on drag due to lift factors of plane and cambered wings included.
Transonic aerodynamic characteristics of wing-body combination having 52.5° sweptback wing of aspect ratio 3 with conical camber and designed for Mach number of 2 root
NASA -- Tech Note
1961
51 pages
Report
English
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