Correction factor methodologies have been developed which use steady experimental or analytical pressure or force data to correct steady and unsteady aerodynamic calculations. Three methods of calculating correction factors have been developed to match steady surface pressure distributions, to match airfoil section forces and moments. Data for a rectangular supercritical wing that was previously tested in the NASA Langley Research Center Transonic Dynamics Tunnel have been used to determine correction factors to match surface pressure distributions for a range of Mach numbers.


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    Title :

    Methodology for Matching Experimental and Computational Aerodynamic Data


    Contributors:

    Publication date :

    1988


    Size :

    13 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English