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타이틀	FACTORS AFFECTING INLET-ENGINE COMPATIBILITY DURING AIRCRAFT DEPARTURES AT HIGH ANGLE OF ATTACK FOR AN F/A-18A AIRCRAFT
저자	W. G. Steenken, J. G. Williams, A. J. Yuhas and K. R. Walsh
Keyword	Aircraft departures; F-18 aircraft; F/A-18A; High angle of attack; Inlet distortion; Inlet-engine compatibility
URL	http://www.dfrc.nasa.gov/DTRS/1999/PDF/H-2327.pdf
보고서번호	NASA-TM-1999-206572
발행년도	1999
출처	NASA Dryden Flight Research Center
ABSTRACT	The F404-GE-400 engine powered F/A-18A High Alpha Research Vehicle (HARV) was used to examine the quality of inlet airflow during departed flight maneuvers, that is, during flight outside the normal maneuvering envelope where control surfaces have little or no effectiveness. A series of six nose-left and six nose-right departures were initiated at Mach numbers between 0.3 and 0.4 at an altitude of 35 kft. The yaw rates at departure recovery were in the range of 40 to 90 degrees per second. Engine surges were encountered during three of the nose-left and one of the nose-right departures. Time-variant inlet-total-pressure distortion levels at the engine face were determined to not significantly exceed those measured at maximum angle-of-attack and -sideslip maneuvers during controlled flight. Surges as a result of inlet distortion levels were anticipated to initiate in the fan. Analysis revealed that the surges initiated in the compressor and were the result of a combination of high levels of inlet distortion and rapid changes in aircraft motion. These rapid changes in aircraft motion are indicative of a combination of engine mount and gyroscopic loads being applied to the engine structure that impact the aerodynamic stability of the compressor through changes in the rotor-to-case clearances.