Inlet flow-field and Internal performance data were obtained for a 0.095-scale model of a vertical/short take-off and landing fighter/attack aircraft configuration with twin top-mounted inlets. The model was tested in the Ames Research Center 11- by 11-Foot Transonic and 9- by 7-Foot Supersonic Wind Tunnels. The effects on the flow field of inlet location, canopy-dorsal integration, wing leading-edge extension (LEX) planform area, variable incidence canards, and wing leading-and trailing-edge flap-deflections were measured. A brief discussion of the results is presented:a more thorough analysis is presented elsewhere.nTests were conducted at Mach numbers from 0.6 to 2.0 and at angles of attack and sideslip up to 27° and 12°, respectively. Reynolds number was held constant at 9.8x10" per meter. Total pressure measurements were obtained in the inlet flow field just upstream from the inlet lip.
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