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Aerodynamic Database Development for the Hyper-X Airframe Integrated Scramjet Propulsion ExperimentsThis 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.
Document ID
20000092515
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Engelund, Walter C. (NASA Langley Research Center Hampton, VA United States)
Holland, Scott D. (NASA Langley Research Center Hampton, VA United States)
Cockrell, Charles E., Jr. (NASA Langley Research Center Hampton, VA United States)
Bittner, Robert D. (FDC/NYMA, Inc. Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2000
Subject Category
Aerodynamics
Report/Patent Number
AIAA Paper 2000-4006
Meeting Information
Meeting: Applied Aerodynamics
Location: Denver, CO
Country: United States
Start Date: August 14, 2000
End Date: August 17, 2000
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.

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