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.
Flight and Static Exhaust Flow Properties of an F110-GE-129 Engine in an F-16XL Airplane During Acoustic Tests
1996-11-01
Report
No indication
English
The F110 engine monitoring system
AIAA | 1984
|SPECIAL SECTION: PREDICTION OF F-16XL FLIGHT-FLOW PHYSICS - Prediction of F-16XL Flight-Flow Physics
Online Contents | 2009
|F110 completes F-15 tests - Engine should quality in '97
Online Contents | 1996
Introduction: Prediction of F-16XL Flight Flow Physics
NTRS | 2009
|