An assessment of the influence of airfoil geometry on delta wing leading edge vortex flow and vortex induced aerodynamics at supersonic speeds is discussed. A series of delta wing wind tunnel models were tested over a Mach number range from 1.7 to 2.0. The model geometric variables included leading edge sweep and airfoil shape. Surface pressure data, vapor screen, and oil flow photograph data were taken to evaluate the complex structure of the vortices and shocks on the family of wings tested. The data show that airfoil shape has a significant impact on the wing upper surface flow structure and pressure distribution, but has a minimal impact on the integrated upper surface pressure increments.


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    Title :

    Influence of Airfoil Geometry on delta Wing Leading-Edge Vortices and Vortex-Induced Aerodynamics at Supersonic Speeds


    Contributors:
    R. M. Wood (author) / J. E. Byrd (author) / G. F. Wesselmann (author)

    Publication date :

    1992


    Size :

    86 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English