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: Monograph (Technical Report)
Uncontrolled Keywords: Panel methods;Sharp corners
Subjects: ENGINEERING > Fluid Mechanics and Thermodynamics
Depositing User: Users 20 not found.
Date Deposited: 28 Jun 2006
Last Modified: 24 May 2010 04:12
URI: http://nal-ir.nal.res.in/id/eprint/1590

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