Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 [degrees] 38' Sweptback Wing of Aspect Ratio 2.98 PDF Download
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Author: Kenneth P. Spreemann
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
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![Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 [degrees] 38' Sweptback Wing of Aspect Ratio 2.98 PDF](https://books.google.com/books/content/images/frontcover/sIOlPgAACAAJ?fife=w80-h100)
Author: Kenneth P. Spreemann
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
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Book Description
Author: Kenneth P. Spreeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
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Author: George L. Pratt
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 110
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Author: William J. Jr Alford
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Author: Kenneth P. Spreeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Author: Lynn W. Hunton
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Author: Nasa Technical Reports Server (Ntrs)
Publisher: BiblioGov
ISBN: 9781289265007
Category :
Languages : en
Pages : 34
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A small-scale transonic investigation of two semispan wings of the same plan form was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range of 0.70 to 1.10 and a mean-test Reynolds number range of 745,000 to 845,000 to determine the effects of partial-span leading-edge camber on the aerodynamic characteristics of a swept-back wing. This paper presents the results of the investigation of wing-alone and wing-fuselage configurations of the two wings; one, was an uncambered wing and the other had the forward 45 percent of the chord cambered over the outboard 55 percent of the span. The semispan wings had 50deg 38ft sweepback of their quarter-chord lines, aspect ratio of 2.98, taper ratio of 0.45, and modified NACA 64A-series airfoil sections tapered in thickness ratio. Lift, drag, pitching moment, and root-bending moment were obtained for these configurations. The results indicated that, for the wing-alone configuration, use of the partial-span leading-edge camber provided an increase in maximum lift-drag ratios up to a Mach number of 0.95, after which no gain was realized. For the wing-fuselage combination, the partial-span leading-edge camber appeared to cause no gain in maximum lift-drag ratio throughout the test range of Mach numbers. The lift-curve slopes of the partial-span leading-edge camber configurations indicated no significant change over the basic configurations in the subsonic range but resulted in slight reductions at the higher Mach numbers. No significantly large changes in pitching-moment-curve slopes or lateral center of additional loading were indicated because of the modification.
Author: Emma Jean Landrum
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52
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Author: George L. Pratt
Publisher:
ISBN:
Category :
Languages : en
Pages : 104
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Author: George L. Pratt
Publisher:
ISBN:
Category :
Languages : en
Pages :
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