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An aerodynamic study of scramjet fuel injectorsThe aerodynamic drag and fuel distribution patterns of injectors designed for a supersonic combustion ramjet were measured at Mach numbers of 2, 2.5, and 3. The most significant parameter effecting the drag was found to be the injector thickness ratio. A two-fold reduction in the thickness ratio caused a 65 percent decrease in drag. Changing the injector sweep angle a factor of 2 resulted in only a small change in drag. A reversal of injector sweep, from sweepback to sweepforward, did not change the measured drag. Helium gas was injected through the struts to simulate the penetration and spreading patterns of hydrogen. Sampling measurements were made at approximately 2 duct heights downstream of the combustor. The spacing required between fuel injectors was found to be about 10 jet diameters. The effect of gas injection on the measured drag was found to be minor.
Document ID
19740009390
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Povinelli, L. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-71504
E-7849
Meeting Information
Meeting: Symp. on the Fluid Mech. of Combustion
Location: Montreal
Start Date: May 13, 1974
End Date: May 16, 1974
Sponsors: ASME, Can. Soc. of Mech. Eng.
Accession Number
74N17503
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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