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: | Mr. N A |
| 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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