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Some Effects of Wing Planform on Sonic BoomA wind-tunnel investigation was conducted to determine the effect of wing planform on sonic boom at Mach numbers of 1.7, 2.0, and 2.7. The results of the investigation show that the wing leading-edge sweep is one of the primary planform variables affecting the overpressure characteristics.
Document ID
19730006982
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Hunton, L. W. (NASA Ames Research Center Moffett Field, CA, United States)
Hicks, R. M. (NASA Ames Research Center Moffett Field, CA, United States)
Mendoza, J. P. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1973
Subject Category
Physics, General
Report/Patent Number
NASA-TN-D-7160
A-4491
Accession Number
73N15709
Funding Number(s)
PROJECT: RTOP 136-13-02-01-00-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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