Experimental studies on isolated supersonic air-intake models of a typical air-breathing launch vehicle

Suryanarayana, GK and Sivaramakrishnan, AE and Priyadarshi, Pankaj and Ganesan, VR (2001) Experimental studies on isolated supersonic air-intake models of a typical air-breathing launch vehicle. In: 15th International Symposium on Air Breathing Engines, 3-7 Sept 2001, Bangalore, India.

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The performance of two supersonic air-intake configurations, S1 and S2, has been extensively analyzed through qualitative and quantitative measurements at Mach numbers in the range 1.8 to 3.0. The exit area of the intake was varied during the tests using a butterfly valve, which was controlled using a PC. The performance of S2 was found to be comparable with that of a standard supersonic intake, with characteristic features of supercritical and subcritical behavior, whereas S1 configuration did not indicate any critical condition. The critical condition for S2 was found to occur when the exit area was about 1.24 times the throat area at M = 3.0. The measured total pressure recovery with S2 was found to be marginally higher than that for S1, whereas the mass flow rate through the intake showed considerable improvement (e.g., 11 percent at M = 3.0 and 19 percent at M = 2.0 at maximum pressure recovery condition). Similar improvements were found with the S2 configuration at other Mach numbers also. It is proposed that an Intake Performance Index (product of the pressure recovery and mass flow efficiencies), as a function of the back-pressure, may be used to compare the efficiencies of different intake configurations. (Author)

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Launch vehicles;Air breathung engines;Supersonic combustion;Air intake;Butterfly valves;Emgime tests;Mathematical models; Performance assessment pressure
Subjects: ASTRONAUTICS > Space Transportation and Safety
Depositing User: M/S ICAST NAL
Date Deposited: 06 Sep 2006
Last Modified: 24 May 2010 04:20
URI: http://nal-ir.nal.res.in/id/eprint/2630

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