Lift and Drag on Cone Cylinders PDF Download
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Author: Theodore Conrad Nark
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 98
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Book Description
Author: Theodore Conrad Nark
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 98
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Book Description
Author: J. Pike
Publisher:
ISBN:
Category :
Languages : en
Pages : 15
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Book Description
Author: L. E. Schmidt
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 36
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Book Description
Author: Jim A. Penland
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 50
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Book Description
Author: JIM A. PENLAND
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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Book Description
Force tests of a series of right circular cones having semivertex angles ranging from 5 to 45 degrees and a series of right circular cone-cylinder configurations having semivertex angles ranging from 5 to 20 degrees and an afterbody fineness ratio of 6 have been made in the Langley 11inch hypersonic tunnel at a Mach number of 6.83, a Reynolds number of 0.24 x 10 to the 6th power per inch, and angles of attack up to 130 degrees. An analysis of the results made use of the Newtonian and modified Newtonian theories and the exact theory. A comparison of the experimental data of both cone and cone-cylinder configurations with theoretical calculations shows that the Newtonian concept gives excellent predictions of trends of the force characteristics and the locations with respect to angle of attack of the points of maximum lift, maximum drag, and maximum lift-drag ratio. Both the Newtonian and exact theories give excellent predictions of the sign and value of the initial lift-curve slope. (Author).
Author: Carl E. Grigsby
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 28
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Book Description
Abstract: An investigation of the Reynolds number for transition and the skin-friction drag at zero lift of eight cone-cylinder bodies having varying fineness ratios has been made at Mach numbers of 1.62, 1.93, and 2.41 over a Reynolds number range from 0.3 x 106 to 10 x 106. The accuracy of the skin-friction data was not sufficient to permit any general conclusions to be drawn. The Reynolds number for transition was found to be dependent upon both the tunnel stagnation pressure and Mach number.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
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Book Description
Author: Robert J. McGhee
Publisher:
ISBN:
Category : Blunt bodies
Languages : en
Pages : 50
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Book Description
Author: D. Adamson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
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Book Description
Author: A. S. Kaye
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 34
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Book Description
