30 degree injectors at hypervelocity conditions

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.