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Measurements of the Basic SR-71 Airplane Near-Field SignatureAirplane design studies have developed configuration concepts that may produce lower sonic boom annoyance levels. Since lower noise designs differ significantly from other HSCT designs, it is necessary to accurately assess their potential before HSCT final configuration decisions are made. Flight tests to demonstrate lower noise design capability by modifying an existing airframe have been proposed for the Mach 3 SR-71 reconnaissance airplane. To support the modified SR-71 proposal, baseline in-flight measurements were made of the unmodified aircraft. These measurements of SR-71 near-field sonic boom signatures were obtained by an F-16XL probe airplane at flightpath separation distances ranging from approximately 740 to 40 ft. This paper discusses the methods used to gather and analyze the flight data, and makes comparisons of these flight data with CFD results from Douglas Aircraft Corporation and NASA Langley Research Center. The CFD solutions were obtained for the near-field flow about the SR-71, and then propagated to the flight test measurement location using the program MDBOOM.
Document ID
20000027450
Acquisition Source
Armstrong Flight Research Center
Document Type
Conference Paper
Authors
Haering, Edward A., Jr.
(NASA Dryden Flight Research Center Edwards, CA United States)
Whitmore, Stephen A.
(NASA Dryden Flight Research Center Edwards, CA United States)
Ehernberger, L. J.
(NASA Dryden Flight Research Center Edwards, CA United States)
Date Acquired
August 19, 2013
Publication Date
December 1, 1999
Publication Information
Publication: High-Speed Research: 1994 Sonic Boom Workshop. Configuration, Design, Analysis and Testing
Subject Category
Aircraft Design, Testing And Performance
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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