Location and mode of transition from laminar to turbulent boundary layer flow have a dominant effect on the aerodynamic characteristics of an airfoil section. The influences of these parameters on the sectional lift and drag characteristics of three airfoils are examined. Both analytical and experimental results demonstrate that when the boundary layer transitions near the leading edge as a result of surface roughness, extensive trailing-edge separation of the turbulent boundary layer may occur. If the airfoil has a relatively sharp leading-edge, leading-edge stall due to laminar separation can occur after the leading-edge suction peak is formed. These two-dimensional results are used to examine the effects of boundary layer transition behavior on airplane longitudinal and lateral-directional stability and control.


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    Title :

    Natural laminar flow and airplane stability and control


    Contributors:


    Publication date :

    1986-05-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Natural laminar flow experiments on modern airplane surfaces

    Holmes, B. J. / Obara, C. J. / Yip, L. P. | NTRS | 1984


    Natural laminar flow experiments on modern airplane surfaces

    Holmes, Bruce J. / Obara, Clifford J. / Yip, Long P. | TIBKAT | 1984


    Natural Laminar Flow Experiments on Modern Airplane Surfaces

    B. J. Holmes / C. J. Obara / L. P. Yip | NTIS | 1984