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Stability and control characteristics of a monoplannar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86An experimental wind tunnel investigation has been made to determine the longitudinal and lateral aerodynamic stability and control characteristics of two tail fin arrangements of a monowing missile model. Both a conventional cruciform and a low profile tail arrangement were tested. The results indicate that the tail surfaces of both configurations were effective in producing pitch control. It was also concluded that both are effective in producing roll and yaw control that is accompanied by proverse yaw and roll, respectively. The conventional cruciform tail produces the most roll and yaw control.
Document ID
19770022140
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Blair, A. B., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1977
Subject Category
Aeronautics (General)
Report/Patent Number
L-11459
NASA-TM-X-3533
Accession Number
77N29084
Funding Number(s)
PROJECT: RTOP 505-11-22-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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