The Effects of Reynolds Number, Mach Number, Spin Rate, and Other Variables on the Aerodynamics of Spheres at Subsonic and Transonic Velocities PDF Download
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Author: C. M. Sabin
Publisher:
ISBN:
Category : Sphere
Languages : en
Pages : 32
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Book Description
Author: C. M. Sabin
Publisher:
ISBN:
Category : Sphere
Languages : en
Pages : 32
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 408
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Book Description
Author: United States. Wright Air Development Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 300
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Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 102
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Book Description
Author: Walter F. Braun
Publisher:
ISBN:
Category : Firearms
Languages : en
Pages : 216
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Book Description
Author: Barbara J. Short
Publisher:
ISBN:
Category : Sphere
Languages : en
Pages : 44
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Book Description
Author: John M. Swihart
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 46
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Book Description
Abstract: The effects of varying Reynolds number on the pressure distribution over a transonic body of revolution are presented. Angles of attack from -2° to 15° were investigated through a Mach number range from 0.60 to 1.09. The Reynolds number based on body length varied from 9 x 106 to 39 x 106, and on maximum diameter from 1.35 x 105 to 4.53 x 105. There were small effects of Reynolds number on the axial pressure distributions of these bodies. These effects were of such a nature as to cause an increase of 0.05 in the normal-force coefficient of the body when tested in the subcritical cross-flow Reynolds number range. A comparison between values of incremental pressure coefficient due to angle of attack and theoretical values was made.
Author: American Astronautical Society
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 1014
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Author: Richard Lehnert
Publisher:
ISBN:
Category :
Languages : en
Pages : 12
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Book Description
Base-pressure measurements were made on spheres with diameters from 0.7925 to 19.99 cm at M = 1.57 to 5.0 to study Mach and Reynolds number effects between Re = 0.06 x 10 to the 6th power and 1.4 x 10 to the 6th power. The data showed that the base-pressure component of the total-drag coefficient is a function of the Reynolds number and can be affected by boundary-layer disturbances. The estimated Reynolds number effect on the total-drag coefficient was very small: a maximum of 10% at M = 1.57 and a minimum of 1% at M = 4.24. The effects of Mach number on wave- and base-drag coefficients cancelled each other so that the total-drag coefficient was almost independent of Mach number. The good agreement between wake configurations determined from wind-tunnel schlieren photographs and firing-range shadowgraphs at correponding Mach and Reynolds numbers suggested the extension of comparative tests with spheres to higher Reynolds numbers in both the wind tunnel and firing range. The failure to detect a critical Reynolds number for spheres at supersonic speeds was attributed to supersonic turbulent separation effects similar to those for subsonic regions.
Author: Richard D. Wagner (Jr.)
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
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Book Description
Exact inviscid pressure distributions and shock shapes, obtained by the method of characteristics, are compared with experimental data. The results indicate a strong dependence of induced pressures upon Reynolds number, especially in the region immediately downstream of the nose-cylinder junction. The measured shock shapes revealed no discernible effect of Reynolds number variations.
