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Test description and preliminary pitot-pressure surveys for Langley Test Technique Demonstrator at Mach 6A propulsion/airframe integration experiment conducted in the NASA Langley 20-Inch Mach 6 Tunnel using a 16.8-in.-long version of the Langley Test Technique Demonstrator configuration with simulated scramjet propulsion is described. Schlieren and vapor screen visualization of the nozzle flow field is presented and correlated with pitot-pressure flow-field surveys. The data were obtained at nominal free-stream conditions of Re = 2.8 x 10 exp 6 and a nominal engine total pressure of 100 psia. It is concluded that pitot-pressure surveys coupled to schlieren and vapor-screen photographs, and oil flows have revealed flow features including vortices, free shear layers, and shock waves occurring in the model flow field.
Everhart, Joel L. (NASA Langley Research Center Hampton, VA, United States) Ashby, George C., Jr. (NASA Langley Research Center Hampton, VA, United States) Monta, William J. (NASA Langley Research Center Hampton, VA, United States)
August 15, 2013
July 1, 1992
Research And Support Facilities (Air)
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