24th Congress of International Council of the Aeronautical Sciences, 29 August-3, September 2004, Yokohama, Japan
Paper ICAS 2004-4.1.4

REYNOLDS NUMBER, COMPRESSIBILITY, AND LEADING-EDGE BLUNTNESS EFFECTS ON DELTA-WING AERODYNAMICS

J. M. Luckring
NASA Langley Research Center, Hampton, Virginia, U.S.A.

Keywords: Aerodynamics, Reynolds Number, Compressibility, Vortex Flow, High Angle of Attack

An overview of Reynolds number, compressibility, and leading edge bluntness effects is presented for a 65 degree delta wing. The results of this study address both attached and vortex-flow aerodynamics and are based upon a unique data set obtained in the NASA-Langley National Transonic Facility. The data were obtained so as to isolate the subject effects and they present many challenges for Computational Fluid Dynamics studies.

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