A numerical procedure for efficient computations near sharp trailing edges of three dimensional wings

Srivastava, Ashok (1993) A numerical procedure for efficient computations near sharp trailing edges of three dimensional wings. Technical Report. National Aerospace Laboratories, Bangalore, India.

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    Abstract

    A numerical procedure has been developed for accurate13; predictions of pressure distribution near sharp trailing edges of three-dimensional wings by applying a flow stagnation condition .The surface integral approach using quadrilateral where the geometry is smooth and continuous .13; vortex panels with Neumann boundary condition has been used on real surfaces Auxiliary panels are introduced near sharp trailing edges to impose a stagnation condition at discontinuous points on the trailing edges resulting in better pressure distribution and more accurate prediction of induced drag . The flow is assumed to be steady, irrotational, inviscid and incompressible .

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Panel methods;Sharp corners
    Subjects: ENGINEERING > Fluid Mechanics and Thermodynamics
    Division/Department: Computational and Theoretical Fluid Dynamics Division
    Depositing User: Mr. N A
    Date Deposited: 28 Jun 2006
    Last Modified: 24 May 2010 09:42
    URI: http://nal-ir.nal.res.in/id/eprint/1590

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