The design and test at Mach number 2.5 of two low-wave-drag ring-wing configurations of aspect ratio 1.3 and 2.6

by Frederick K. Browand, Beverly Jane Beane, Daniel T. Nowland

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Development of an analytic design procedure for contouring complete-ring-body supersonic aerodynamic configurations that cancel nearly all the zero-lift wave (thickness) drag. Wind-tunnel tests, conducted at Mach number 2.5 on two ring-body configurations, verify the design procedure. The results of measurements of the performances of the test models at angle of attack are included.

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