Yajnik, KS and Subbaiah, MV (1975) On the representation of the drag polar of a fighter aircraft. Technical Report. National Aeronautical Laboratory, Bangalore, India.
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Abstract
The values of lift coefficient encountered during manoeuvres13; of a fighter aircraft are known to be wel1 beyond the range where the classical representation CD = CDo + k ci is a good approximation. Examination of available test data on several configurations showed that the drag polars can be approximately represented as CD = CDo + k ci + a C with a suitable choice of a and n.13; A simpler representation with the value of n equal to 413; was carefully tested against detailed test data on two configurations for Mach numbers ranging from 0.5 to 1.5 and angles of attack from -4xB0; to 20xB0;. Agreement was generally better than 5% in transonic and supersonic range. The agreement was satisfactory in the subsonic range, although the departures were occasionally larger in magnitude. It is suggested that the representation with n = 4 can be advantageously used in the turn calculations of fighter aircrafts.
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Manoeuvres;Drag polars;Subsonic range |
| Subjects: | AERONAUTICS > Aerodynamics |
| Division/Department: | Aerodynamics, Aerodynamics |
| Depositing User: | M/S ICAST NAL |
| Date Deposited: | 14 Nov 2006 |
| Last Modified: | 24 May 2010 09:49 |
| URI: | http://nal-ir.nal.res.in/id/eprint/2580 |
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