Flight-Measured Effects of Boattail Angle and Mach Number on the Nozzle Afterbody Flow of a Twin-Jet Fighter. Meeting Paper AIAA-1980-0110, Research Engineering, NASA Dryden Flight Research Center
Plant, Thomas J. and Nugent, Jack and Davis, Robert A. (1980) Flight-Measured Effects of Boattail Angle and Mach Number on the Nozzle Afterbody Flow of a Twin-Jet Fighter. Meeting Paper AIAA-1980-0110, Research Engineering, NASA Dryden Flight Research Center.
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Abstract
This paper presents the flight-measured nozzle afterbody surface pressures and engine exhaust nozzle pressure-area integrated axial force coefficients on a twin-jet fighter for varying boattail angles. The objective of the tests was to contribute to a full-scale flight data base applicable to the nozzle afterbody drag of advanced tactical fighter concepts. The data were acquired during the NASA F-15 Propulsion/Airframe Interactions Flight Research Program. Nozzle boattail angles from 7.7° to 18.1° were investigated. Results are presented for cruise angle of attack at Mach numbers from 0.6 to 2.0 at altitudes from 20,000 to 45,000 feet. The data show the nozzle axial force coefficients to be a strong function of nozzle boattail angle and Mach number.
| EPrint Type: | Other |
|---|---|
| Keywords: | F-15 aircraft |
| Subjects: | Aircraft/Project: F-15 |
| ID Code: | 1591 |
| Deposited On: | 13 June 2007 |
| Additional Information: | 13 pages. AIAA 18th Aerospace Sciences Meeting, Pasadena, California, January 14-16, 1980. |
