An overview of two nonlinear supersonic wing design studiesThe progress of two studies which apply nonlinear aerodynamics to supersonic wing design is reviewed. The first study employed a nonlinear potential flow code to design wings for high lift and low drag due to lift by employing a controlled leading-edge expansion in which the crossflow accelerates to supercritical conditions and decelerates through a weak shock. The second study utilized a modified linearized theory code to explore the concept of using 'attainable' leading-edge thrust as a guide for selecting a wing leading-edge shape (planform and radius) for maintaining attached flow and maximizing leading-edge thrust. Experimental and theoretical results obtained during the course of these two studies are discussed.
Document ID
19830047131
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Miller, D. S. (NASA Langley Research Center Hampton, VA, United States)
Pittman, J. L. (NASA Langley Research Center Hampton, VA, United States)
Wood, R. M. (NASA Langley Research Center High-Speed Aerodynamics Div., Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 83-0182
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting