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 35 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section

Author: Henry, Beverly Z., Jr.
Year: 1950
Document Type: N/A
Series: NACA Research Memorandums
Report Number: NACA-RM-L50J09
Link: https://digital.library.unt.edu/ark:/67531/metadc58761/

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