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Dynamic response of Mach 2.5 axisymmetric inlet with 40 percent supersonic internal area contraction (1973)

Neiner, G. H. ; Batterton, P. G. ; Baumbick, R. J. ; [et al.]

In: CASI

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Publication Date: 2019-06-27

Description: Results of experimental tests conducted on a supersonic, mixed compression, axisymmetric inlet are presented. The inlet is designed for operation at Mach 2.5 with a turbofan engine (TF-30). The inlet was terminated with either a choked-orifice plate or a long pipe with variable area choked exit plug. Frequency responses were obtained for selected static pressures in the diffuser. These pressures were selected as potential control signals for terminal shock control. Frequency responses were obtained for the Mach 2 and 2.5 conditions for different terminations. Responses also were obtained with and without cowl bleed. Internal disturbances were produced by sinusoidally varying the inlet overboard bypass doors at frequencies out to 100 hertz.

Keywords: PROPULSION SYSTEMS

Type: NASA-TM-X-2833 , E-7426

Format: application/pdf

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