Abstract
Abstract : A double-oblique-shock scramjet model has been developed using the AEDC-VKF 16-in. Shock Tunnel I at a free-stream Mach number of 11. The model was developed as a test bed for the development of instrumentation and hydrogen fuel injection techniques for supersonic combustion experiments to be conducted at the 54-in. test section in the AEDC-VKF Tunnel F. Difficulties were encountered, especially at the entrance to the combustor because of the combined action of separation and the interaction of the second shock from the cowl lip. Considerable effort was expended before these influences were reduced to the point that the flow in the combustor was satisfactory. The results of these development tests are reported here.
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