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SUBCRITICAL FLOW STUDIES ON 2-DIMENSIONAL EXTERNAL COMPRESSION SUPERSONIC INLETS

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Title SUBCRITICAL FLOW STUDIES ON 2-DIMENSIONAL EXTERNAL COMPRESSION SUPERSONIC INLETS
 
Creator KAPOOR, K
PAI, TG
PAMADI, BN
 
Description An experimental study has been carried out to develop a subcritical flow model to predict the additive drag and stable flow range of two-dimensional external compression supersonic inlets. Two variable geometry inlet models have been tested in a 0.3-m trisonic wind tunnel at Mach number varying from 1.6 to 2.2. The inlet mass flow was varied in the steady subcritical flow range and the total pressure recovery, ramp pressure distribution and mass flow ratio were measured. The corresponding shock stand-off distance was obtained from schlieren pictures. Based on these experimental data, a new subcritical now model that correlates the inlet geometry, shock stand-off distance, and freestream Mach number has been developed.
 
Publisher AMER INST AERONAUT ASTRONAUT
 
Date 2011-07-15T10:30:20Z
2011-12-26T12:49:26Z
2011-12-27T05:48:50Z
2011-07-15T10:30:20Z
2011-12-26T12:49:26Z
2011-12-27T05:48:50Z
1992
 
Type Article
 
Identifier JOURNAL OF PROPULSION AND POWER, 8(4), 849-856
0748-4658
http://dx.doi.org/10.2514/3.23559
http://dspace.library.iitb.ac.in/xmlui/handle/10054/4242
http://hdl.handle.net/10054/4242
 
Language en