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Pressure distributions on three different cruciform aft-tail control surfaces of a wingless missile at mach 1.60, 2.36, and 3.70 Volume 1: Trapezoidal tailThe results of pressure distribution tests conducted in the Langley Unitary Plan wind tunnel are presented. The data were obtained for three sets of cruciform aft-tail control surfaces on a wingless missile model at Mach numbers of 1.60, 2.36, and 3.70 for angles of attack from -4 degrees to 20 degrees, model roll angles from 0 degrees to 90 degrees, and tail deflections of 0 degrees and 15 degrees. The test Reynolds number used was 6.6 million per meter.
Document ID
19790018928
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Lamb, M. (NASA Langley Research Center Hampton, VA, United States)
Sawyer, W. C. (NASA Langley Research Center Hampton, VA, United States)
Wassum, D. L. (NASA Langley Research Center Hampton, VA, United States)
Babb, C. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
L-12993
NASA-TM-80097-VOL-1
Accession Number
79N27099
Funding Number(s)
PROJECT: RTOP 505-11-23-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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