Pressure distributions on a semi span rectangular wing model having an NACA 0015 airfoil section and a moderate aspect ratio were measured at one spanwise station in tests made on a transonic bump in the Ames 16-foot high- speed wind tunnel. The free-stream Mach number range was from 0.4 to 1.06. The results showed that at a fixed angle of attack a region developed over the airfoil wherein the Mach number at each point remained essentially constant as the free-stream Mach number was increased above the critical. This region covered essentially the whole chord of the airfoil at free-stream Mach numbers near unity.


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    Title :

    Flow About a Section of a Finite-Aspect-Ratio NACA 0018 Airfoil on a Transonic Bump


    Contributors:

    Publication date :

    1953


    Size :

    31 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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    Mellenthin, J.A. | Engineering Index Backfile | 1953




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