Hypersonic nozzle-afterbody experiment: Flow visualization and boundary-layer measurements

This study was conducted to characterize experimentally the flowfield created by he interaction of a single-expansion-ramp nozzle flow with a hypersonic external stream. Data were obtained from a generic nozzle-afterbody model in the 3.5 Ft Hypersonic Wind Tunnel of the NASA Ames Research Center in a cooperative experimental program involving NASA Ames and McDonnell Douglas Corporation, The model design and test planning were performed in close cooperation with members of the Ames computational fluid dynamics (CFD) team for the National Aero-Space Plane Program, Experimental results are! presented, consisting of oil-how and shadowgraph flow-visualization photographs, afterbody surface-pressure distributions, forebody and nozzle boundary-layer rake measurements, and Preston-tube-skin-friction measurements. The oil flows sow the outward turning of the underexpanded jet al the cowl exit, and the interaction of a jet-plume internal shock with the nozzle boundary layer Shadowgraph photographs show the forebody boundary layer, shock waves in the external Row and the jet, and the shear layer between the jet and the external-flow. These data are available for CFD code validation.