Experimental Investigation at a Mach Number of 3.11 of the Lift, Drag, and Pitching-moment Characteristics of Five Blunt Lifting Bodies PDF Download
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Author: William Letko
Publisher:
ISBN:
Category : Lift (Aerodynamics)
Languages : en
Pages : 18
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Book Description
Author: William Letko
Publisher:
ISBN:
Category : Lift (Aerodynamics)
Languages : en
Pages : 18
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Book Description
Author: Vernard E. Lockwood
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
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Book Description
Author: Russell W. McDearmon
Publisher:
ISBN:
Category : Axial loads
Languages : en
Pages : 38
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Book Description
Author: Jim A. Penland
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 31
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Book Description
Results are presented of three-component force tests of a cylindrical body with an ogival nose equipped with panel-type drag brakes each covering approximately 21 percent of the body circumference and located on opposite sides of the body at the rear end. The investigation was made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.86, a Reynolds number of 1,500,000 based on body length, angles of attack from -5 to 25 degrees, and brake-deflection angles from 0 to 30 degrees, with the brakes in the vertical and horizontal planes. The comparison of experimental results with the results of Newtonian impact theory shows that the trends of the longitudinal characteristics with angle of attack may be predicted with reasonable accuracy. The drag brakes in the vertical position produce higher total drag and higher negative pitching moments at angles of attack than do the identical brakes in the horizontal position, even though the top drag brake becomes ineffective at high angles of attack.
Author: Hyman Harvey Album
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 164
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Book Description
The force and moment characteristics of spiked bodies with hemispherical, hemispherical-flat, and flat noses were determined in a supersonic wind tunnel at angles of attack from zero to 10 degrees. The afterbodies were right circular cylinders. A fineness ratio of 3 was maintained for all of the basic bodies. The spikes were of five different configurations and ranged in length from 0.75 to 2.0 body diameters. Freestream conditions included Mach numbers from 2.0 to 3.0 and Reynolds numbers from 300,000 to 900,000 (based on body diameter). It was found that the spikes greatly reduced the zero-angle drag, made the drag extremely sensitive to angle of attack variations, substantially increased the lift, and also increased the normal force. The body nose shape proved to be a critical factor in determining the magnitude of these characteristics and whether or not the spikes would have a stabilizing effect on the body pitching moment characteristics. (Author).
Author: Jon S. Pyle
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 36
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Book Description
Author: Dean R. Chapman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 92
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Book Description
Summary: Tests were conducted to determine the effects of viscosity on the drag and base pressure characteristics of various bodies of revolution at a Mach number of 1.5. The models were tested both with smooth surfaces and with roughness added to evaluate the effects of Reynolds number for both laminar and turbulent boundary layers. The principal geometric variables investigated were after-body shape and length-diameter ratio. For most models, force tests and base pressure measurements were made over a range of Reynolds numbers, based on model length, from 0.6 million to 5.0 millions. Schlieren photographs were used to analyze the effects of viscosity on flow separation and shock-wave configuration near the base and to verify the condition of the boundary layer as deduced from force tests. The results are discussed and compared with theoretical calculations.
Author: K. D. Harris
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 30
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 54
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Book Description
Author: Edward W. Perkins
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 56
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Book Description
This report contains the results of an experimental investigation to determine the effects of support interference on the base drag and fore drage of two bodies of revolution. The results show that the rear supports affect the drag of a body of revolution through the immediate influence on the pressures acting over the rear portions of the body and thus the magnitude of the interference depends on the afterbody shape of the model, the Reynolds number of flow, and the condition of the boundary layer.
