Compressible linear boundary-layer stability analyses of two representative axisymmetric fuselage geometries indicate that a favorable effect will be exerted on the characteristics of a fuselage's axisymmetric boundary layer by compressibility. A freestream Mach number increase from 0.6 to 0.8 significantly reduces TS wave growth rates in the laminar boundary layer of the fuselages analyzed. The generally destabilizing effect of increasing length Re number on boundary layer stability can be overpowered by the favorable effects of compressibility on the fluid.


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    Title :

    Effects of compressibility on design of subsonic fuselages for natural laminar flow


    Contributors:

    Published in:

    Publication date :

    1988-09-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    EFFECTS OF COMPRESSIBILITY ON DESIGN OF SUBSONIC NATURAL LAMINAR FLOW FUSELAGES

    VIJGEN, P. M. / DODBELE, S.S. / HOLMES, B.J. et al. | AIAA | 1986


    Effects of compressibility on design of subsonic fuselages for natural laminar flow

    VIJGEN, P. M. H. W. / DODBELE, S. S. / HOLMES, B. J. et al. | AIAA | 1988


    Design of Natural Laminar Flow Fuselages

    Coiro, D. P. / Nicolosi, F. | British Library Online Contents | 1994


    Design of Natural Laminar Flow Fuselages

    Coiro, D. P. / Nicolosi, F. / International Council of Aeronautical Sciences | British Library Conference Proceedings | 1994