Effects of Inlet Distortion on a Static Pressure Probe Mounted on the Engine Hub in an F-15 Airplane
Hughes, Donald L. and Mackall, Karen G. (1984) Effects of Inlet Distortion on a Static Pressure Probe Mounted on the Engine Hub in an F-15 Airplane.
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Abstract
Knowledge of the pressure conditions at the engine face is important for the efficient control of an air-breathing engine. However, there are many problems encountered in obtaining good engine face pressure data. In a special study, a single static measurement located upstream of the engine hub in the stream flow was found to provide a pressure signal suitable for engine control. A probe for measuring fan inlet static pressure (PS2) was designed for and mounted on the hub of the left F100-PW-100 turbofan engine installed in the F-15 test aircraft for flight evaluation at the NASA Ames Research Center Dryden Flight Research Facility (ARC-DFRF) (ref.1). This same probe was also evaluated on the hub of another F100 engine in the NASA Lewis Research Center (LeRC) altitude facility (ref. 2). The probe is currently being used as a static pressure sensor for a digital engine control system (ref. 3).
| EPrint Type: | Other |
|---|---|
| Keywords: | Digital control, Engine control, Flight tests, F-15 airplane, F100 engine. |
| Subjects: | (01 - 09) Aeronautics: (07) Aircraft Propulsion And Power Aircraft/Project: F-100 |
| ID Code: | 2025 |
| Deposited On: | 15 July 2009 |
| Additional Information: | 17 pages. NASA CP-2298, Paper 5, Digital Electronic Engine Control Flight Evaluation in an F-15 Airplane, pp. 73-89, March 1984. |
