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Transonic Aerodynamic Loading Characteristics of a Wing-Body-Tail Combination Having a 52.5 deg. Sweptback Wing of Aspect Ratio 3 With Conical Wing Camber and Body Indentation for a Design Mach Number of Square Root of 2An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5 deg. with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0 deg. to 14 deg., with Reynolds numbers based on mean aerodynamic chord varying from 7 x 10(exp 6) to 8 x 10(exp 6). Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced the transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
Document ID
19980227081
Acquisition Source
Headquarters
Document Type
Other - NASA Technical Note (TN)
Authors
Cassetti, Marlowe D. (NASA Langley Research Center Hampton, VA United States)
Re, Richard J. (NASA Langley Research Center Hampton, VA United States)
Igoe, William B. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1961
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-971
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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