Tables for Supersonic Flow of Helium Around Right Circular Cones at Zero Angle of Attack PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Tables for Supersonic Flow of Helium Around Right Circular Cones at Zero Angle of Attack PDF full book. Access full book title Tables for Supersonic Flow of Helium Around Right Circular Cones at Zero Angle of Attack by Joseph L. Sims. Download full books in PDF and EPUB format.
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
Get Book Here
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 : 36
Get Book Here
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 : 38
Get Book Here
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 : 462
Get Book Here
Book Description
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 422
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 444
Get Book Here
Book Description
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1152
Get Book Here
Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1252
Get Book Here
Book Description
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1102
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 276
Get Book Here
Book Description
Author: Mitchel H. Bertram
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 32
Get Book Here
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.
