Aerodynamic database development for the Hyper-X airframe-integrated scramjet propulsion experiments

An overview of the activities associated with the aerodynamic database that is being developed in support of NASA's Hyper-X scramjet flight experiments is provided. Three flight tests are planned as part of the Hyper-X program. Each will utilize a small, non-recoverable research vehicle with an airframe-integrated scramjet propulsion engine. The research vehicles will be individually rocket boosted to the scramjet engine test points at Mach 7 and 10. The research vehicles will then separate from the first stage booster vehicle and the scramjet engine test will be conducted before the terminal decent phase of the flight. An overview is provided of the activities associated with the development of the Hyper-X aerodynamic database, including wind-tunnel test activities and parallel computational fluid dynamics analysis efforts for all phases of the Hyper-X flight tests. A brief summary of the Hyper-X research vehicle aerodynamic characteristics is provided, including the direct and indirect effects of the airframe-integrated scramjet propulsion system operation on the basic airframe stability and control characteristics. Brief comments on the planned postflight data analysis efforts are also included.