A subsonic and a transonic airfoil are presented for application in a high-altitude long-endurance aircraft and a very-high-altitude aircraft, respectively. The subsonic airfoil is designed for a lift coefficient c(l) = 1.4 at a chord Reynolds number Re = 700,000 and a very low Mach number. The transonic airfoil is designed for c(l) = 1.0 at Re = 500,000 and a transonic Mach number M = 0.7. Both airfoils are developed to perform as well or better than previously designed airfoils. However, the present airfoils are developed for a constrained pitching moment to reduce aircraft trim drag and to relieve, to some extent, the torsional loads in the typically high-aspect-ratio wings. The beneficial effects of a cruise flap and of boundary-layer transition control on the off-design performance characteristics are illustrated.


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    Title :

    Subsonic and transonic low-Reynolds-number airfoils with reduced pitching moments


    Contributors:
    Van Dam, C. P. (author) / Hicks, R. (author) / Reuther, J. (author)

    Publication date :

    1990-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :