Recent applications of numerical optimization to the design of advanced airfoils for transonic aircraft have shown that low-drag sections can be developed for a given design Mach number without an accompanying drag increase at lower Mach numbers. This is achieved by imposing a constraint in the drag coefficient at an off-design Mach number while the drag at the design Mach number is the objective function. Such a procedure doubles the computation time over that for single design-point problems, but the final result is worth the increased cost of computation, The ability to treat such multiple designpoint problems by numerical optimization has been enhanced by the development of improved airfoil shape functions. Such functions permit a considerable increase in the range of profiles attainable during the optimization process.


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    Title :

    Application of numerical optimization to the design of supercritical airfoils without drag-creep


    Additional title:

    Numerische Optimierung bei der Konstruktion superkritischer Tragflaechen ohne Stroemungswiderstand


    Contributors:

    Published in:

    Publication date :

    1977


    Size :

    11 Seiten, 11 Bilder, 13 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Application of Numerical Optimization to the Design of Supercritical Airfoils without Drag-Creep

    Vanderplaats, Garret N. / Hicks, Raymond M. | SAE Technical Papers | 1977



    Thick supercritical airfoils with low drag and natural laminar flow

    EGGLESTON, B. / POOLE, R. J. D. / JONES, D. J. et al. | AIAA | 1987


    Comparison of Theory and Experiment for Four Supercritical, Low Drag Airfoils

    D. J. Jones / M. Khalid / B. Eggleston | NTIS | 1988