A Transonic-wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-fuselage Configuration Having a Wing of 60 Degree Sweepback, Aspect-ratio 4, Taper Ratio 0.6, and NACA 65A006 Airf
1951-01-24
Miscellaneous
No indication
English