An experimental study has been performed to assess the maximum lift capability of a supercritical multielement airfoil representative of an advanced transport aircraft wing. The airfoil model was designed with a leading-edge slat and single or two-segment trailing-edge flaps. Optimization work was performed at various slat/flap deflections as well as gap/overhang positions. Landing configurations and the attainment of maximum lift coefficients of 4.5 with single-element flaps and 5.0 with two-segment flaps was emphasized. Test results showed a relatively linear variation of the optimum gap/overhang positioning of the slat versus slat deflection, considerable differences in optimum rigging between single and double segment flaps, and large Reynolds number effects on multielement airfoil optimization.


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    Title :

    Multi-element airfoil optimization for maximum lift at high Reynolds numbers



    Conference:

    AIAA Applied Aerodynamics Conference


    Publication date :

    1991-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Multielement Airfoil Optimization for Maximum Lift at High Reynolds Numbers

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    Multi-element airfoil optimization for maximum lift at high Reynoldsnumbers

    VALAREZO, WALTER / DOMINIK, CHET / MCGHEE, ROBERT et al. | AIAA | 1991