This report examines transonic flows over an airfoil which was partially modified from an arbitrary airfoil. Modifications were made to satisfy the shockless condition. Static pressures were measured at 88 points on an airfoil surface at Mach numbers from 0.5 to 0.8 with the angle of attack from 0 to 4 degree and the Reynolds number from 4.0 to 4.6 million. A shockless transonic flow was observed under a test condition close to the design condition. The supersonic region extends from 0.3% to 63% of airfoil chord length and the local maximum Mach number is 1.36. The result of this experiment supports the artificial flow method for obtaining shockless transonic airfoils which are partially modified from an arbitrary airfoil.


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    Title :

    Experiment of a Shockless Transonic Airfoil


    Contributors:
    M. Nakamura (author) / K. Suzuki (author) / S. Nakamura (author) / M. Shirai (author)

    Publication date :

    1983


    Size :

    12 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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