Flight measurements obtained with a TF-8A airplane modified with a supercritical wing are presented for altitudes from 7.6 kilometers (25,000 feet) to 13.7 kilometers (45,000 feet), Mach numbers from 0.6 to 1.2, and Reynolds numbers from 0.8 x 10 to the 7th power to 2.3 x 10 to the 7th power. Flight results for the airplane with and without area-rule fuselage fairings are compared. The techniques used to determine the lift and drag characteristics of the airplane are discussed. Flight data are compared with wind-tunnel model results, where applicable.


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    Title :

    Flight Determined Lift and Drag Characteristics of an F-8 Airplane Modified with a Supercritical Wing with Comparison to Wind-Tunnel Results


    Contributors:
    J. S. Pyle (author) / L. L. Steers (author)

    Publication date :

    1975


    Size :

    87 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English