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A Whitham-Theory Sonic-Boom Analysis of the Tu-144 Aircraft at a Mach Number of 2.2NASA became interested in the Tu- 144 aircraft when it was offered for use as a "flying testbed" to study operating characteristics of a supersonic-cruise commercial airplane. In addition to the other operational tests being conducted on the Tu- 144 aircraft, it was proposed that two sets of sonic-boom pressure signature measurements be made. One set of tests would consist of ground-level pressure measurements. The second set would be measurements of pressures under the Tu- 144 aircraft in cruise. Pressure gages would be required for this second set of tests: measuring ambient and differential pressures in the flow field of a Tu-144 cruising at supersonic speeds. The range of these gages had to be determined well in advance of the scheduled flights so that they could be installed and calibrated.
Document ID
20000027648
Acquisition Source
Langley Research Center
Document Type
Contribution to a larger work
Authors
Robert J Mack
(Langley Research Center Hampton, Virginia, United States)
Date Acquired
August 19, 2013
Publication Date
December 1, 1999
Publication Information
Publication: 1995 NASA High-Speed Research Program Sonic Boom Workshop: Volume II - Configuration Design, Analysis, and Testing
Publisher: National Aeronautics and Space Administration
Volume: 2
Subject Category
Aerodynamics
Meeting Information
Meeting: NASA High-Speed Research Program Sonic Boom Workshop
Location: Hampton, VA
Country: US
Start Date: September 11, 1995
End Date: September 13, 1995
Sponsors: Langley Research Center
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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