[PDF] Performance And Control Of A Full Scale Axially Symmetric External Internal Compression Inlet From Mach 20 To 30 eBook

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Performance of External-internal Compression Inlet with Abrupt Internal Turning at Mach Numbers 3.0 to 2.0

Leonard J. Obery
Performance of External-internal Compression Inlet with Abrupt Internal Turning at Mach Numbers 3.0 to 2.0 by Leonard J. Obery PDF

Author : Leonard J. Obery
Publisher :
Page : 21 pages
File Size : 26,69 MB
Release : 1957
Category : Aerodynamics, Supersonic
ISBN :

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An inlet with combined external and internal compression, formed by spike and cowl oblique shocks, and an over-all length of 2.5 inlet diameters was investigated at Mach numbers from 3.0 to 2.0 over a range of angles of attack. At the design Mach number of 3.0 the low angle cowl, which turned the flow supersonically, generated two internal shocks and focused them on the centerbody surface. These compression waves, with their high pressure gradient, were cancelled by abrupt centerbody turning. This investigation showed that with proper boundary-layer control on the centerbody this method of internal compression did not adversely affect the high performance of the inlet.

Experimental Investigation of a Large-scale, Two-dimensional, Mixed-compression Inlet System

Norman D. Wong
Experimental Investigation of a Large-scale, Two-dimensional, Mixed-compression Inlet System by Norman D. Wong PDF

Author : Norman D. Wong
Publisher :
Page : 68 pages
File Size : 44,86 MB
Release : 1971
Category : Jet engines
ISBN :

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A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.