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: Eugene D. Schult
Publisher:
ISBN:
Category : Fins (Anatomy)
Languages : en
Pages : 32
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Book Description
This paper discusses the rolling effectiveness of deflected fins, flaps, spoilers, and jet devices which may be employed on fin-stabilized vehicles. The possible applications and some of the significant factors affecting the performance of each device are described. The experimental information has been published previously and was obtained chiefly from free-flight tests of fin-stabilized vehicles at Mach numbers up to approximately 2.0. Comparisons are made in some cases with existing theory, which is also relied upon to indicate trends where data are not available.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1208
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Book Description
