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An Integrated Fuselage-Sting Balance for a Sonic-Boom Wind-Tunnel ModelMeasured and predicted pressure signatures from a lifting wind-tunnel model can be compared when the lift on the model is accurately known. The model's lift can be set by bending the support sting to a desired angle of attack. This method is simple in practice, but difficult to accurately apply. A second method is to build a normal force/pitching moment balance into the aft end of the sting, and use an angle-of-attack mechanism to set model attitude. In this report, a method for designing a sting/balance into the aft fuselage/sting of a sonic-boom model is described. A computer code is given, and a sample sting design is outlined to demonstrate the method.
Document ID
20040191553
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Mack, Robert J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
November 1, 2004
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA/TM-2004-213265
L-19041
Funding Number(s)
WORK_UNIT: WU 23-065-10-91
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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