Aerodynamic Interference of Slender Wing-tail Combinations PDF Download
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Author: Alvin H. Sacks
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 81
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Book Description
Mathematical expressions are derived for the interference forces and moments acting on the tails of slender plane and cruciform wing-tail combinations of general plan form in steady straight flight at combined angles of attack and sideslip. The derivatives are made within the limitations of slender-body theory under the assumption that the vortex sheet leaves the wing as flat sheet and becomes fully rolled up ahead of the tail. The derived expressions are used to calculate the steady lifts, side forces, pitching moments, and rolling moments of the number of wing-tail combinations. The effects of changes in tail height, tail length, ratio of tail span to wing span, tail incidence, and tail thickness are calculated. The resulting curves, and particularly their nonlinearities, are discussed at some length in connection with static stability. In general, the most dramatic effects are noted when the vortices shed from the wing strike the tips of the tail trailing edge.
Author: Alvin H. Sacks
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 81
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Book Description
Mathematical expressions are derived for the interference forces and moments acting on the tails of slender plane and cruciform wing-tail combinations of general plan form in steady straight flight at combined angles of attack and sideslip. The derivatives are made within the limitations of slender-body theory under the assumption that the vortex sheet leaves the wing as flat sheet and becomes fully rolled up ahead of the tail. The derived expressions are used to calculate the steady lifts, side forces, pitching moments, and rolling moments of the number of wing-tail combinations. The effects of changes in tail height, tail length, ratio of tail span to wing span, tail incidence, and tail thickness are calculated. The resulting curves, and particularly their nonlinearities, are discussed at some length in connection with static stability. In general, the most dramatic effects are noted when the vortices shed from the wing strike the tips of the tail trailing edge.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
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Book Description
Author: Jack N. Nielsen
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 676
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Book Description
The wing-body interference theory of NACA TN 2677 applied to symmetrical wings in combination with quasi-cylindrical bodies permits the direct calculation of pressure-distribution changes produced by body shape changes. This theory is used to determine the relative magnitued of the wave-drag reduction produced by changes in cylinder cross-sectional area and that produced changes in cross-sectional shape (without change in area). The body distortion is expressed as a Fourier series, and an integral equation is derived for the body shape for minimum drag for each Fourier component. Thus the wave-drag reductions for the various Fourier harmonics are independent and additive.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
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Author: P.R. Owen
Publisher:
ISBN:
Category :
Languages : en
Pages : 64
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Author: Albert Sherman
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 110
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Author: Alvin Howard Sacks
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 454
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Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages :
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Author: Steven I. Kane
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 74
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Book Description
The problem of predicting the induced roll phenomena associated with finned missiles at high angles of attack has been approached by examining the interaction between the body wake vortex system and the finned surfaces of the missile. The application of the classic Blasius moment integral to this problem permits the independent evaluation of each singularity in the flow field which may contribute to the moments. This method is applicable to missiles employing fin schemes of any geometry and is used herein to analyze the induced roll of a typical cruciform missile configuration. A computer program has been developed to generate numerical solutions utilizing those parameters which affect the magnitude and direction of the induced roll. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
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