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F-12 Inlet Development
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English
Abstract
The aerodynamic design of the F-12 engine air inlet is discussed following development from its inception to the present configuration. A description of the various tests related to the inlet is presented, along with some of the tests results. The importance of engine, inlet, and ejector matching is discussed. Close coordination between the airframe and engine manufacturer allowed the selection of an airframe-mounted ejector with inherent performance advantages. The nozzle requirements affected the final selection of the inlet bleed system. Early testing of inlet distortion on the engine compressor rig helped provide adequate engine stall margins. Comparison of early one-eighth scale model data with recent NASA test and flight data is included.
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Citation
Campbell, D., "F-12 Inlet Development," SAE Technical Paper 740831, 1974, https://doi.org/10.4271/740831.Also In
References
- Luidens Roger W. Flaherty Richard J. “Use of Shock Trap Bleed to Improve Pressure Recovery of Fixed and Variable-Capture-Area Internal Contraction Inlets; Mach Number 2.0 and 3.0.” NACA RM E 58D 24 August 1958
- Campbell David H. “F-12 Series Aircraft Propulsion System Performance and Development.” AIAA Paper 73-821, 5th Aircraft Design, Flight Test and Operations Meeting St. Louis August 1973
- Obery Leonard J. Stitt Leonard E. “Performance of External-Internal Compression Inlet with Abrupt Internal Turning at Mach Numbers 3.0 to 2.0.” NACA RM E 57H 07a October 1957
- Cnossen J. W. “Studies of Boundary Layer Removal Scoops for High Performance Supersonic Inlets.” United Aircraft Corp. Rept. R-0955-21
- Smeltzer Donald B. Smith Ronald H. Cubbison Robert W. “Wind Tunnel and Flight Performance of the YF-12 Inlet System.” AIAA Paper 74-621, 8th Aerodynamic Testing Conf. Bethesda, Mo. July 1974