Viswanathan, S (1991) Application of a panel code for in house aircraft projects: Part I. Technical Report. National Aeronautical Laboratory, Bangalore, India.
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Abstract
The panel code NALSOF0509 (available in the SOFFTS library13; at NAL) can compute the chordwise and spanwise load distributions, centre of pressure locations on the wing, shift of the aerodynamic centre due to the fuselage and overall aerodynamic coefficients. This code is presently used to generate data on the aircraft configurations like NALLA and LTA, and for the delta wing-body tested in the 1ft.x1ft. tunnel of the Experimental Aerodynamics Division. The code is also validated against the tunnel results available for AGARD-B model. This report describes in brief some of these experience.
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Panel method;Wing-body combination;Delta wing |
| Subjects: | AERONAUTICS > Aircraft Design, Testing & Performance |
| Division/Department: | Computational and Theoretical Fluid Dynamics Division |
| Depositing User: | Mr. Ravikumar R |
| Date Deposited: | 13 Jul 2006 |
| Last Modified: | 24 May 2010 09:44 |
| URI: | http://nal-ir.nal.res.in/id/eprint/1839 |
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