Experimental studies on a two-dimensional supersonic mixed compression air intake at mach numbers of 0.76, 1.06, and 1.18

Swamy, Shivakumara M and Dutta, AC and Ahmed, Sajeer (1977) Experimental studies on a two-dimensional supersonic mixed compression air intake at mach numbers of 0.76, 1.06, and 1.18. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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Abstract

To investigate the performance improvements, due to a13; simple throat bleed system, in supersonic mixed compression13; intake, a 2-D model was tested in the I-ft tunnel of HAL.13; The results at off-design Mach numbers viz. M = 0.76, 1.06,13; and 1.18 are reported here. (Results at close to the design13; Mach number have already been reported in AE-TM-8-76).13; The test program covered mass flow ratios from zero to the13; maximum, under three representative bleed conditions. The13; investigation has revealed that the performance of the intake at these off-design Mach numbers can be significantly improved by even a simplest throat bleed system. Improvements in the total pressure recovery, distortion index and the maximum mass flow ratio have been noticed, with a bleed mass equal to a small fraction of the total mass. Further,it is also noticed that the throat bleed has a definite tendency to improve the stability characteristics of the intake under low mass flow operations, viz. subcritical flow conditiona which is very13; beneficial from the point of view of intake buzz. Flow13; visualization of both the internal and external flows have13; proved to be very useful tools in interpreting the results13; and also understanding the flow phenomenon.

Item Type: Monograph (Technical Report)
Uncontrolled Keywords: Throat bleed system;Two-dimensional supersonic
Subjects: AERONAUTICS > Aerodynamics
Depositing User: Users 90 not found.
Date Deposited: 30 Aug 2006
Last Modified: 24 May 2010 04:19
URI: http://192.168.9.127/id/eprint/2603

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