NASA NTRS · 19930039016
Shock-dependent, thrust wings for supersonic flow
Abstract
A new wing concept which lowers the inviscid drag of a wing in supersonic flow is described. The thrust-wing concept uses a secondary shock that occurs to the rear of the maximum thickness location to produce a significant aerodynamic thrust force from the rearward portion of the wing, thus reducing the inviscid drag. The evaluation of the thrust-wing concept is conducted on a delta-wing planform of differing sweep angles and thicknesses at Mach 1.60 over a wide range of lifting conditions.
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Pittman, James L.. 1993-01-01. Shock-dependent, thrust wings for supersonic flow. https://ntrs.nasa.gov/citations/19930039016
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