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Author: Alvin H. Sacks
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 702
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Book Description
It is found that the impulse of each shed vortex and its image vortex in a transformed circle plane enters into all the interference forces and moments on the airplane. A simple theorem is given for the interference forces in steady straight flight which are found to depend on this impulse evaluated only at the wing trailing edge and at the base of the configuration.
Author: Alvin H. Sacks
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 702
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Book Description
It is found that the impulse of each shed vortex and its image vortex in a transformed circle plane enters into all the interference forces and moments on the airplane. A simple theorem is given for the interference forces in steady straight flight which are found to depend on this impulse evaluated only at the wing trailing edge and at the base of the configuration.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1322
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
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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 : 900
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 534
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: George G. Edwards
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 658
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Book Description
An investigation has been conducted at speeds up to a Mach number of 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration having a 40 degrees swept wing with an aspect ratio of 10. Results of wind-tunnel tests of a model representing such an airplane configuration (see NACA TN 3789) show that these effects are of most concern in the low-speed high-thrust flight regime. In the present report the low-speed data are analyzed to determine the source of the various effects and to indicate how the adverse effects can be reduced, and the high-speed data are discussed primarily from the standpoint of Mach number effects. The analysis of the low-speed data indicates that the large variations of longitudinal stabil.itywith angle of attack resulted primarily from passage of the tail into and out of the slipstream. The slipstream also created large lift increments on the wing, particularly with flaps deflected, which resulted in increases in stability (with increasing thrust coefficient) from the outboard propeller and decreases in stability from the inboard propeller. It was concluded that the longitudinal stabiltty characteristics of the model couldbe improved by moving the nacelles outward, increasing the tail height, and reducing the tail span.
