Theoretical Damping in Roll and Rolling Effectiveness of Slender Cruciform Wings PDF Download
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Author: Gaynor J. Adams
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 40
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Book Description
The coefficients of damping in roll and rolling effectiveness (with differential incidence of the horizontal surfaces) are determined for a slender, equal-span, cruciform wing. It is found that the coefficient of damping in ar roll is 62 percent greater than for a plane slender wing of equal aspect ratio, and that the rolling effectiveness is 53 percent less than for a plane slender wing of equal aspect ratio. The analysis can be used in the estimation of the characteristics of a slender, equal-span, cruciform wing having any specified distribution of normal velocity components on the horizontal and vertical surfaces.
Author: Gaynor J. Adams
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 40
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Book Description
The coefficients of damping in roll and rolling effectiveness (with differential incidence of the horizontal surfaces) are determined for a slender, equal-span, cruciform wing. It is found that the coefficient of damping in ar roll is 62 percent greater than for a plane slender wing of equal aspect ratio, and that the rolling effectiveness is 53 percent less than for a plane slender wing of equal aspect ratio. The analysis can be used in the estimation of the characteristics of a slender, equal-span, cruciform wing having any specified distribution of normal velocity components on the horizontal and vertical surfaces.
Author: Arthur W. Goldstein
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 236
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 22
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Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 540
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Author: James Benjamin Delano
Publisher:
ISBN:
Category : Propellers, Aerial
Languages : en
Pages : 724
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Book Description
This paper presents propeller characteristics for two propellers that differ only in inboard pitch distribution. The forward Mach number range extended to 0.062 and the blade-angle range was from 20 to 55 degrees. Section thrust-coefficient data are also presented to afford a more detailed analysis of the effects of modifying the pitch distribution of the inboard sections of a propeller.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1498
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 432
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1200
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Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1208
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 516
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