Flight and Static Exhaust Flow Properties of an F110-GE-129 Engine in an F-16XL Airplane During Acoustic Tests
Holzman, Jon K. and Webb, Lannie D. and Burcham Jr., Frank W. (1996) Flight and Static Exhaust Flow Properties of an F110-GE-129 Engine in an F-16XL Airplane During Acoustic Tests. Technical Report NASA TM-104326, Research Engineering, NASA Dryden Flight Research Center.
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Abstract
The exhaust flow properties (mass flow, pressure, temperature, velocity, and Mach number) of the F110-GE-129 engine in an F-16XL airplane were determined from a series of flight tests flown at NASA Dryden Flight Research Center, Edwards, California. These tests were performed in conjunction with NASA Langley Research Center, Hampton, Virginia (LaRC) as part of a study to investigate the acoustic characteristics of jet engines operating at high nozzle pressure conditions. The range of interest for both objectives was from Mach 0.3 to Mach 0.9. NASA Dryden flew the airplane and acquired and analyzed the engine data to determine the exhaust characteristics. NASA Langley collected the flyover acoustic measurements and correlated these results with their current predictive codes. This paper describes the airplane, tests, and methods used to determine the exhaust flow properties and presents the exhaust flow properties. No acoustics results are presented.
| EPrint Type: | NASA Technical Memorandum |
|---|---|
| Keywords: | Acoustics, Exhaust, F110 engine, F-16XL airplane, Flyover noise |
| Subjects: | (01 - 09) Aeronautics: (07) Aircraft Propulsion And Power Aircraft/Project: F-16XL |
| ID Code: | 200 |
| Deposited On: | 16 July 2004 |
| Additional Information: | 29 pages. |
