Computation of inviscid transonic flow past aerofoils using body fitted coordinates

Subramanian, NR and Chakrabartty, SK (1984) Computation of inviscid transonic flow past aerofoils using body fitted coordinates. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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    Abstract

    Several numerical methods exist for solving two-dimensional transonic full potential equations, appear due to conservative or non-conservative forms of equations, satisfying boundary conditions on the surface of the body13; by extra polation or by using body fitted curvilinear coordinates obtained by different methods. Holst solved the conservative full potential equation fortransonic flow past arbitrary airfoil s and developed the TAD? code. The object of this work is to adapt the code to the existing computers (DZ 1090 and UNIVAC ll00/60HI) and try it out on various conventional and super critical airfoils Modifications are then introduced to improve the prediction of pressure distribution and shock position on13; super critical airfoils having extended regions of supersonic The differences flow , A suitable second order artificial viscosity term has been presented here and introduced in TAIR to get a second order accurate solution throughout the flow field except at the shock wave position , where it reverts to first order. The modified13; version of the code STAIR has been added are in the annexure.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Inviscid transonic flow;Viscosity
    Subjects: ENGINEERING > Fluid Mechanics and Thermodynamics
    AERONAUTICS > Aerodynamics
    Division/Department: Flight Mechanics and Control Division, Flight Mechanics and Control Division
    Depositing User: M/S ICAST NAL
    Date Deposited: 14 Sep 2006
    Last Modified: 24 May 2010 09:50
    URI: http://nal-ir.nal.res.in/id/eprint/2727

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