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A Study of Panel Loads and Centers of Pressure of Three Different Cruciform Aft-Tail Control Surfaces of a Wingless Missile from Mach 1.60 to 3.70An investigation was made of the forces and moments on the cruciform aft-tail control surfaces of a wingless missile model to determine the variation of panel load and center of pressure with angle of attack, tail deflection, model roll angle, and Mach number. Also, a limited force-moment and surface-pressure investigation was made on a noncircular aft end. These investigations were made in a unitary plan wind tunnel at Mach numbers of 1.60, 2.36, and 3.70 and at a Reynolds number per meter of 6,600,000. The cruciform aft-tail results indicate very little variation in the center of pressure for the highly loaded windward tail. The noncircular aft-end test results indicate no significant effect of the fin unporting on the fin loads.
Document ID
19800014762
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Lamb, M. (NASA Langley Research Center Hampton, VA, United States)
Trescot, C. D., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
May 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-81787
L-13501
Accession Number
80N23251
Funding Number(s)
PROJECT: RTOP 505-43-23-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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