Influence of wing geometry on leading-edge vortices and vortex-induced aerodynamics at supersonic speedsAn assessment of the influence of wing geometry on wing leading-edge vortex flows at supersonic speeds is discussed as well as the applicability of various aerodynamic codes for predicting these results. A series of delta-wing wind-tunnel models were tested in the NASA Langley Research Center Unitary Plan Wind Tunnel over a Mach number range from 1.6 to 4.6. The data show that wing airfoil has a significant impact on the localized loading on the wing. The experimental data for the flat wings were compared with results from full-potential, Euler, and Parabolized Navier-Stokes (PNS) computer codes. The theoretical evaluation showed that the full-potential analysis predicted accurate results for the attached-flow (alpha = 0 deg) conditions and that the Euler and PNS analyses made reasonable predictions for both attached and separated flow conditions.
Document ID
19890037704
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wood, Richard M. (NASA Langley Research Center Hampton, VA, United States)
Bauer, Steven X. S. (NASA Langley Research Center Hampton, VA, United States)
Byrd, James E. (NASA Langley Research Center Hampton, VA, United States)
Mcgrath, Brian E. (Planning Research Corp. Hampton, VA, United States)
Wesselmann, Gary F. (NASA Langley Research Center Hampton, VA; USAF, Arnold Engineering Development Center, Arnold AFB, TN, United States)