This paper provides an overview of the activities associated with the aerodynamic database which is being developed in support of NASA's Hyper-X scramjet flight experiments. Three flight tests are planned as part of the Hyper-X program. Each will utilize a small, nonrecoverable 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 Mach 10. The research vehicles will then separate from the first stage booster vehicle and the scramjet engine test will be conducted prior to 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 CFD 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 post flight data analysis efforts are also included.
Aerodynamic Database Development for the Hyper-X Airframe Integrated Scramjet Propulsion Experiments
2000
30 pages
Report
Keine Angabe
Englisch
Aerodynamics , Test Facilities & Equipment , Airframes , Computational fluid dynamics , Data bases , Flight tests , Supersonic combustion ramjet engines , Aerodynamic characteristics , Wind tunnel tests , Research vehicles , Aerodynamic configurations , Rudders , Engine tests , X-43 vehicle , Hypersonic speed , Postflight analysis