Damping in Roll of Cruciform and Some Related Delta Wings at Supersonic Speeds PDF Download
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Author: Herbert S. Ribner
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 50
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Book Description
The damping in roll of cruciform delta wings in supersonic flow has been evaluated by means of small-disturbance (linearized) wing theory; both subsonic and supersonic component stream velocities normal to the leading edges have been considered. In addition, some known two-dimensional results for rotating multibladed laminae have been applied to obtain the loading when the number of panels is changed from four to an arbitrary number, under the restriction of low aspect ratio; the damping in roll has been determined explicitly for three panels. Finally, the damping for an inifinite number of panels has been evaluated without restriction as to aspect ratio or Mach number.
Author: Herbert S. Ribner
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 50
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Book Description
The damping in roll of cruciform delta wings in supersonic flow has been evaluated by means of small-disturbance (linearized) wing theory; both subsonic and supersonic component stream velocities normal to the leading edges have been considered. In addition, some known two-dimensional results for rotating multibladed laminae have been applied to obtain the loading when the number of panels is changed from four to an arbitrary number, under the restriction of low aspect ratio; the damping in roll has been determined explicitly for three panels. Finally, the damping for an inifinite number of panels has been evaluated without restriction as to aspect ratio or Mach number.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 480
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Book Description
Author: Arthur W. Goldstein
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 236
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
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Book Description
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: F. B. Gustafson
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 720
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Book Description
Part 1 of this report presents a brief review of methods available to the helicopter designer for obtaining desired stability characteristics by modifications to the airframe design. The discussion is based on modifications made during the establishment of flying-qualities criteria and includes sample results of theoretical studies of additional methods. The conclusion is reached that it is now feasible to utilize combinations of methods whereby stability-parameter values are realized which in turn provide the desired stability characteristics. Part 2 reviews some of the methods of predicting rotor stability derivatives. The procedures by which these rotor derivatives are employed to estimate helicopter stability characteristics have been summarized.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1200
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Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: S. S. Chin
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 304
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Book Description
Beskriver principperne i f.m. konstruktionen af styrede missiler.
Author: A. E. Potter
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 358
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Book Description
Author: Walter G. Walker
Publisher:
ISBN:
Category : Acceleration (Mechanics)
Languages : en
Pages : 642
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Book Description
This paper presents the results of an analysis of approximately 100,000 hours of V-G data from one type of four-engine civil transport airplane to determine the magnitude and frequency of occurrence of the gust loads and gusts. The data were obtained during routine operations from 1947 to 1954 on five different routes. The normal accelerations for each of the five operations may be expected to exceed the value corresponding to the limit-gust-load-factor increment, on the average, twice (once positive and once negative) within the range of 5,000,000 to 22,300,000 flight miles. A derived gust velocity of 50 feet per second was exceeded twice within the range of 600,000 to 1,900,000 flight miles. The gust loads of the present operations were less than the loads experienced by other four-engine civil transports previously investigated, but the differences are not significant. The present data indicated only small differences due to seasonal effects and different operational utilization.
