Aerodynamic Characteristics of the Sharp Right Circular Cone at Mach 20.3 and Angles of Attack to 110 ̊in Helium PDF Download
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Author: Dal V. Maddalon
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 60
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Book Description
Author: Dal V. Maddalon
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 60
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Book Description
Author: Dal V. Maddalon
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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Book Description
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 38
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Book Description
The results of the calculation of supersonic flow of helium about right circular cones at zero angle of attack are presented in tabular form. The calculations were performed using the Taylor-Maccoll theory. Numerical integrations were performed using a Runge-Kutta method for second-order differential equations. Results were obtained for cone angles from 2.5 to 30 degrees in regular increments of 2.5 degrees. In all calculations the desired free-stream Mach number was obtained to five or more significant figures.
Author: Theodore R. Creel
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 42
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Author: Jim A. Penland
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 50
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Author: Melvin J. Fohrman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
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Author: John K. Molloy
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 44
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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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: Joseph W. Cleary
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 52
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