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 2 PDF Download
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Author: William B. Igoe
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: William B. Igoe
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: William B. Igoe
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 56
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Author: William B. Igoe
Publisher:
ISBN:
Category :
Languages : en
Pages : 51
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Author: William B. Igoe
Publisher:
ISBN:
Category : Aerodynamics, aircraft
Languages : en
Pages : 51
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Author: William B. Igoe
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Author: WILLIAM B. IGOE
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Category :
Languages : en
Pages : 1
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An investigation was 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 quarterchord line sweepback was 52.5 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 to 14. The camberedwing 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. (Author).
Author: MARLOWE D. CASSETTI
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ISBN:
Category :
Languages : en
Pages : 1
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A inves iga io as been made of the effects of conical wing camber and body indentation ccordi g to t e supersonic area rule on the aerodynamic wing loading characteristics of a wingbody-tail configuration at transonic speeds. The wing aspect ratio was 3, aper ratio was 0.1, and quarter-chord-line sweepback was 52.5 deg with 3-perc t- ick airfoil sec ions. The tests were conducted in the Langley 16-foot transonic unnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0 to 14 deg with Rey olds numbers based on mean aerodyna ic chord varying from 7 x 10 to the 6th power to 8 x 10 to the 6th power. Conical camber delayed wing-tip stall and r duced s verity 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 centerof-pressure travel from about 8 percent to 5 percent of the mean aerodyn mic chord. (Author).
Author: Lowell E. Hasel
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Author: Harry W. Carlson
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ISBN:
Category :
Languages : en
Pages : 20
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Author: Melvin M. Carmel
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 60
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