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 (Listing Multiple Pages).
| Filename | Size | Format | Download |
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| 19930086548.pdf | 1.3 MB | application/pdf | Download |