Tables for Supersonic Flow Around Right Circular Cones at Zero Angle of Attack PDF Download
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Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 462
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Book Description
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 462
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Book Description
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 440
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Book Description
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 428
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Book Description
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
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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: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 882
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Book Description
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 422
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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: Mitchel H. Bertram
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 32
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Book Description
Concise accurate graphs of cone flow properties at zero yaw in air as a perfect gas are presented in correlation form. From these graphs the pressure, density, temperature, shock angle, and Mach number may be obtained both at the cone surface and immediately behind the shock, for free-stream Mach numbers from that for shock detachment to that approaching infinity and for cone semi -apex angles up to 50°. In addition, the initial slope of the normal-force curve is given for the same range of conditions.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 616
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 394
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Book Description
