In this paper, an approach for optimum airfoil design is proposed for enhancing the lift to drag ratio with respect to the base NACA 2312 airfoil for subsonic incompressible flow regime at four degree angle of attack. An iterative inverse design method is followed to obtain airfoil for desired lift to drag ratio. Differential evolutionary (DE) optimization technique with micro population and elitism is employed and lift to drag ratio has been increased in two ways: with and without constraint on the maximum thickness. An inviscid-viscous interactive method is used as a flow solver in which vortex panel method is used to solve the inviscid flow; Thwaite’s method is used to get the laminar boundary layer; the transition is determined by Michel’s relation and Head’s method is used to get turbulent boundary layer. The approach is implemented with a user-interactive program developed in MATLAB and effectiveness of optimization scheme is validated with forward design tools.


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    Titel :

    Design of an Effective Subsonic Wing Cross-Section Using Viscous-Inviscid Interactive Method


    Weitere Titelangaben:

    Lect.Notes Mechanical Engineering


    Beteiligte:
    Bajpai, Ram P. (Herausgeber:in) / Chandrasekhar, U. (Herausgeber:in) / Arankalle, Avinash R. (Herausgeber:in) / Prabhu, L. (Autor:in) / Srinivas, J. (Autor:in)


    Erscheinungsdatum :

    03.05.2014


    Format / Umfang :

    6 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch