A procedure for the optimization of supersonic airfoils is presented. A nonlinear, full-potential solver (NCOREL) is coupled with a numerical optimizer (CONMIN). The NCOREL code is a three-dimensional supersonic marching method, however, only two-dimensional (conical) results are used for the airfoil problem. Each airfoil evaluated in the NCOREL aerodynamic code is composed of a linear combination of user-specified basis airfoils. The weighting factors of the basis airfoils plus the angle of attack form the design variable vector. The inviscid drag coefficient is minimized subject to lift and crossflow Mach number gradient constraints. The optimization strategy is found to be extremely important for the efficient determination of an optimum airfoil.


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    Titel :

    Supersonic airfoil optimization


    Beteiligte:
    Pittman, J. L. (Autor:in)

    Erscheinungsdatum :

    01.01.1986


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Supersonic airfoil optimization

    PITTMAN, J. | AIAA | 1986


    Supersonic airfoil optimization

    Pittman, James L. | NTRS | 1987


    Supersonic airfoil optimization

    PITTMAN, JAMES L. | AIAA | 1987


    AIRFOIL FOR SUPERSONIC AIRCRAFT

    O'LEARY PATRICK | Europäisches Patentamt | 2024

    Freier Zugriff

    Approach to supersonic airfoil theory

    Strohmeyer, W.E. / Gero, D.R. | Engineering Index Backfile | 1950