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Experimental Investigation of Inlet-to-Inlet Shock Interference
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English
Abstract
This report describes the experimental program conducted, and presents wind tunnel test data obtained during the comprehensive study of supersonic pod to pod inlet interference. This test established, for a typical Mach 3.0 design mixed compression inlet, the dividing line between the regions of expelled shock interference and completely stable operation and the total pressure recovery penalty imposed by operating with pod to pod interference. The penalty required in order to maintain stability during the initial transient of the onset of “buzz” was so severe that it cannot be considered practical. A plate placed between pods was found to be very effective in eliminating the interference penalty.
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Citation
Motycka, D. and Murphy, J., "Experimental Investigation of Inlet-to-Inlet Shock Interference," SAE Technical Paper 650197, 1965, https://doi.org/10.4271/650197.Also In
References
- Motycka D. L. “The Effect of an Interference Shock on the Performance of a Mach 3.0 Axisymmetric Movable Centerbody Inlet,” January 1962
- Trimpi Robert L. “Air Analysis of Buzzing in Supersonic Ram Jets by a Modified One-Dimensional Nonstationary Wave Theory,” July 1956
- Mirels Harold “Acoustic Analysis of Ram Jet Buzz,” November 1955
- Sterbentz W. H. Davids J. “Amplitude of Supersonic Diffuser Flow Pulsations,” October 1955
- Sterbentz W. H. Evvard J. C. “Criterions of Prediction and Control of Ram-Jet Flow Pulsations,” August 1955
- Motycka D. L. Murphy J. B. “Inlet-to-Inlet Shock Interference Tests,” December 31 1964