NASA supercritical airfoils are characterized by a substantially reduced curvature of the midcord region of the upper surface together with increased camber near the trailing edge. The basic aerodynamic phenomena associated with the airfoils and representative wind tunnel results are discussed. The results indicate that the drag rise Mach numbers for NASA supercritical airfoils are 0.1 higher than for comparable NACA 6-series airfoils. A recent analytic method for predicting the aerodynamic characteristics of supercritical airfoils is described. The flight demonstration programs of three applications of supercritical airfoils utilizing the F-8, T-2C and F-111 as test beds are summarized.


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    Title :

    Review of NASA supercritical airfoils


    Contributors:

    Conference:

    International Council of the Aeronautical Sciences Congress ; 1974 ; Haifa, Israel


    Publication date :

    1974-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :