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 (NTF) for (1) Reynolds numbers ranging from conventional wind-tunnel to flight values, (2) Mach numbers ranging from subsonic to transonic speeds, and (3) leading-edge bluntness values that span practical slender wing applications. The data were obtained so as to isolate the subject effects and they present many challenges for Computational Fluid Dynamics (CFD) studies.


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    Title :

    Reynolds Number, Compressibility, and Leading-Edge Bluntness Effects on Delta-Wing Aerodynamics


    Contributors:

    Publication date :

    2004


    Size :

    18 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English