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Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds Several Combinations of the Tail with Each of Two Foreshortened Body SegmentsAn investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numbers of 1.62 and 1.96 of a partial-span body with one tail surface, designed for use on the Hughes Falcon (MX-904) missile. The present paper extends the work reported in NACA-RM-SL50E10. Force and moment data including elevator hinge moment were obtained for the conditions of the tail in the presence of a small segment of the fore-shortened body, in the presence of a semi-span body and attached to a semi-span body, and for the condition of the foreshortened semi-span body alone.
Document ID
20050029421
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Guy, Lawrence D. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Conner, D. William (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 22, 2013
Publication Date
January 1, 1950
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-SL50G13
Report Number: NACA-RM-SL50G13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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