NASA NTRS · 19920066253
30 degree injectors at hypervelocity conditions
Abstract
Results are presented of the first high-speed propulsion-related experiments performed in the NASA-Ames 16-Inch Shock Tunnel, designed to simulate combustor inlet conditions at approximately Mach 14. Results demonstrate the capability of the tunnel for high-speed propulsion testing and yield data on the performance of 30-deg flush wall injectors tested in the tunnel. The experimental results are compared with those of a CFD analysis.
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Loomis, Mark P., Zambrana, Horacio A., Bogdanoff, David W., Tam, Tim C., Cavolowsky, John A., Newfield, Mark E., Bittner, Robert D.. 1992-07-01. 30 degree injectors at hypervelocity conditions. https://ntrs.nasa.gov/citations/19920066253
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