This paper provides an overview of the experimental aerodynamics test program to ensure mission success for the autonomous flight of the Hyper-X Research Vehicle (HXRV). The HXRV is a 12-ft long, 2700 Ib lifting body technology demonstrator designed to flight demonstrate for the first time a fully airframe integrated scramjet propulsion system. Three flights are currently planned, two at Mach 7 and one at Math 10, beginning in the fall of 2000. The research vehicles will be boosted to the

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... ibed scramjet engine test point where they will separate from the booster, stabilize, and initiate engine test. Following 5+ seconds of powered flight and 15 seconds of cowlopen tares, the cowl will close and the vehicle will fly a controlled deceleration trajectory which includes numerous control doublets tor in-flight aerodynamic parameter identification. This paper reviews the preflight testing activities, wind tunnel models, test rationale, risk reduction activities, and sample results from wind tunnel tests supporting the flight trajectory of the HXRV from hypersonic engine test point through subsonic tlight termination. Nomenclature t_ angle-of-attack (degrees) 13 sideslip angle (degrees) br_f Hyper-X vehicle reference span C D Drag tbrce coefficient ( Dra_ ) " q_oSref *Assistant Branch Head, Aerothermodynamics Branch, Senior Member AIAA. **Aerothermodynamics Branch, Associate Fellow, AIAA. *'*Vehicle Analysis Branch, Senior Member, AIAA.