A Transonic Investigation Of Changing Indentation Design Mach Number On The Aerodynamic Characteristics Of A 45 Sweptback Wing Body Combination Designed For High Performance
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Investigation at Mach Numbers from 0.80 to 1.43 of Pressure and Load Distributions Over a Thin 45° Sweptback Highly Tapered Wing in Combination with Basic and Indented Bodies
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.