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Transonic Aerodynamic Characteristics of a Wing-Body Combination having a 52.5 deg Sweptback Wing of Aspect Ratio 3 with Conical Camber and Designed for a Mach Number of the Square Root of 2An investigation has been made of the effects of conical wing camber and supersonic body indentation on the aerodynamic characteristics of a wing-body configuration at transonic speeds. Wing aspect ratio was 3.0, taper ratio was 0.1, and quarter-chord line sweepback was 52.5 deg with airfoil sections of 0.03 thickness ratio. The tests were conducted in the Langley 16-foot transonic tunnel at various Mach numbers from 0.80 to 1.05 at angles of attack from -4 deg to 14 deg. The cambered-wing configuration achieved higher lift-drag ratios than a similar plane-wing configuration. The camber also reduced the effects of wing-tip flow separation on the aerodynamic characteristics. In general, no stability or trim changes below wing-tip flow separation resulted from the use of camber. The use of supersonic body indentation improved the lift-drag ratios at Mach numbers from 0.96 to 1.05.
Document ID
20040006370
Document Type
Other - NASA Technical Note (TN)
Authors
Igoe, William B. (NASA Langley Research Center Hampton, VA, United States)
Re, Richard J. (NASA Langley Research Center Hampton, VA, United States)
Cassetti, Marlowe (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 21, 2013
Publication Date
May 1, 1961
Subject Category
Aerodynamics
Report/Patent Number
L-1243
NASA-TN-D-817
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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