The VSAERO surface panel method is employed to investigate fuselage shapes which can enhance the natural laminar flow (NLF) characteristics. The study is performed at cruise Re which are relevant to commuter, transport, and business aircraft. The technique is based on piecewise constant doublet and source singularities and takes into account the effects of compressibility. Inviscid pressure distributions were generated for five configurations to aid in the search for an optimized NLF body shape as a function of the transition locations and the drag coefficients. Granville's transition criteria are incorporated into the calculations to yield shapes with longer runs of laminar flow and reduced drag. In comparison with other transition prediction methods, the method described is shown to have significantly higher valicity for making three-dimensional transition predictions.


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    Title :

    Shaping of airplane fuselages for minimum drag


    Contributors:

    Publication date :

    1986-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Shaping of airplane fuselages for minimum drag

    DODBELE, S. / VAN DAM, C. / HOLMES, B. | AIAA | 1986


    Shaping of airplane fuselages for minimum drag

    DODBELE, S. S. / VAN DAM / C. P. et al. | AIAA | 1987


    Shaping of airplane fuselages for minimum drag

    Dodbele, S. S. / Van Dam, C. P. / Vijgen, P. M. H. W. et al. | NTRS | 1987



    Drag reduction of airplane fuselages through shaping by the inverse method

    Zedan, M. F. / Seif, A. A. / Al-Moufadi, S. | AIAA | 1994