Personnel at the NASA Langley Research Center (NASA-Langley) and the NASA Dryden Flight Research Facility (NASA-Dryden) recently completed a joint acoustic flight test program. Several types of aircraft with high nozzle pressure ratio engines were flown to satisfy a twofold objective. First, assessments were made of subsonic climb-to-cruise noise from flights conducted at varying altitudes in a Mach 0.30 to 0.90 range. Second, using data from flights conducted at constant altitude in a Mach 0.30 to 0.95 range, engineers obtained a high quality noise database. This database was desired to validate the Aircraft Noise Prediction Program and other system noise prediction codes. NASA-Dryden personnel analyzed the engine data from several aircraft that were flown in the test program to determine the exhaust characteristics. The analysis of the exhaust characteristics from the F-18 aircraft are reported. An overview of the flight test planning, instrumentation, test procedures, data analysis, engine modeling codes, and results are presented.
Flight-determined engine exhaust characteristics of an F404 engine in an F-18 airplane
AIAA/SAE/ASME/ASEE Joint Propulsion Conference and Exhibit ; 1993 ; Monterey, CA, United States
1993-10-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
F404 Engine Reliability Program
SAE Technical Papers | 1983
|F404 engine reliability program
Tema Archiv | 1983
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