naca-rm-l51f07
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National Advisory Committee for Aeronautics, Research Memorandum - Transonic Wing Investigation in the Langley 8 Foot High Speed Tunnel at High Subsonic Mach Numbers and at a mach Number of 1.2 - Analysis of Pressure Distribution of Wing Fuselage Configuration Having a Wing of 45° Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
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| naca-rm-l51f07 Transonic Wing Investigation in the Langley 8 Foot High Speed Tunnel at High Subsonic Mach Numbers and at a mach Number of 1.2 - Analysis of Pressure Distribution of Wing Fuselage Configuration Having a Wing of 45° Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section.pdf | Download |
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