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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 Degrees Sweptback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
| Author: | Loving, Donald L. |
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| Year: | 1951 |
| Document Type: | N/A |
| Series: | NACA Research Memorandums |
| Report Number: | NACA-RM-L51F07 |
| Link: | https://digital.library.unt.edu/ark:/67531/metadc59039/ |
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