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Experimental Verification Of The Osculating Cones Method For Two Waverider Forebodies At Mach 4 and 6The NASA Langley Research Center Unitary Plan Wind Tunnel and the 20-Inch Mach 6 Tunnel were used to test two osculating cones waverider models. The Mach-4 and Mach-6 shapes were generated using the interactive design tool WIPAR. WIPAR performance predictions are compared to the experimental results. Vapor screen results for the Mach-4 model at the on- design Mach number provide visual verification that the shock is attached along the entire leading edge, within the limits of observation. WIPAR predictions of pressure distributions and aerodynamic coefficients show general agreement with the corresponding experimental values.
Document ID
20040087268
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Miller, Rolf W. (Colorado Univ. Boulder, CO, United States)
Argrow, Brian M. (Colorado Univ. Boulder, CO, United States)
Center, Kenneth B. (Centerstage Animated Reconstructions Lakewood, CO, United States)
Brauckmann, Gregory J. (NASA Langley Research Center Hampton, VA, United States)
Rhode, Matthew N. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 1998
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA Paper 98-0682
Report Number: AIAA Paper 98-0682
Meeting Information
Meeting: 36th Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 12, 1998
End Date: January 15, 1998
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NGT1-52134
Distribution Limits
Public
Copyright
Public Use Permitted.

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