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Inlet Duct—Engine Airflow Match and Compatibility for Supersonic Aircraft
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English
Abstract
A record of excellent compatibility with induction systems of all installations has been established by the J79 engine in six air weapons operating at Mach 2 and above. The paper discusses the aspects of steady state matching, dynamic matching, inflow distortion, and compressor design. Studies show that the engine must be evaluated as a component of the propulsion system, and that dynamic matching is at least as important as steady state matching for air breathing engines at Mach 3 and above.
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Authors
Topic
Citation
Alford, J., Davies, D., and Young, L., "Inlet Duct—Engine Airflow Match and Compatibility for Supersonic Aircraft," SAE Technical Paper 620300, 1962, https://doi.org/10.4271/620300.Also In
References
- Hand W. H. “Compatibility Considerations for a Supersonic Transport Engine Performance Specification,” ASME Paper No. 62-AV-29 June 1962
- Gabriel D. Wallner L. Lubick R. Vasu G. “Some Effects of Inlet Pressure and Temperature Transients on Turbojet Engines,” Aeronautical Engineering Review 16 9 September 1957
- Alford J. S. “Inlet Flow Distortion Index,” International Days of Aeronautical Sciences May 27- 29, 1957 Paris, France
- Alford J. S. “Inlet Duct-Engine Flow Compatibility,” Fifth International Aeronautical Conference IAS June 20-24, 1955
- Smith L. H. Jr. “Recovery Ratio--A Measure of the Loss Recovery Potential of Compressor Stages,” ASME Paper No. 56-A-206
- Pearson H. “Wakes in Axial Compressors,” Journal of the Royal Aeronautical Society July 1959
- Rowe G. T. “Power Plant Requirements for Supersonic Transport,” ASME Paper No. 62-AV-26 June 1962