Investigation of the flow through a single-stage two-dimensional nozzle in the Langley 11-inch hypersonic tunnel

Charles H. McLellan, Thomas W. Williams, Ivan E. Beckwith
naca-tn-2223
Dec 1950


Flow surveys have been made in the second of several nozzles to be investigated in the Langley 11-inch hypersonic tunnel. The single-stage, two-dimensional nozzle was designed by the method of characteristics for a Mach number of 7.08 without boundary-layer corrections.

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