Hypersonic shook-heated flow parameters for velocities to 46,000 feet per second and altitudes to 323,000 feet PDF Download
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Author: Paul William Huber
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages :
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Book Description
Author: Paul William Huber
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages :
Get Book Here
Book Description
Author: Paul William Huber
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 88
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Book Description
![Hypersonic Shock-heated Flow Parameters for Velocities to 46,000 Feet Per Second and Altitudes to 323,000 Feet [with List of References] PDF](https://books.google.com/books/content/images/frontcover/uY0ztAEACAAJ?fife=w80-h100)
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 74
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Book Description
Author: Robert L. Geronime
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 27
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Book Description
Author: Wilbur Clifton Nelson
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 810
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Book Description
Author: Charles George Miller
Publisher:
ISBN:
Category : Gases at high temperatures
Languages : en
Pages : 48
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Book Description
Author: Saul Feldman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 134
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Book Description
A collection of charts is presented for the equilibrium properties of air in several flow situations of interest in hypersonic flow. The cases considered are: (a) flow over bodies in flight at hypersonic speeds: normal and oblique shocks; (b) flow over bodies in shock tubes: this includes moving, standing, and reflected normal shocks as well as oblique shocks. A Mollier diagram is also included.
Author: Paul W. Huber
Publisher:
ISBN:
Category : Shock waves
Languages : en
Pages : 26
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Book Description
Tables and graphs of normal-shock parameters are presented for real air in thermal and chemical equilibrium at conditions ahead of the shock corresponding to six selected altitudes, and for temperatures behind the shock from 2,000 deg K to 11,000 deg K. The altitudes used are those representing the boundaries of the isothermal layers in that part of the earth's atmosphere considered applicable to aerodynamic flight; that is, below an altitude of 300,000 feet. The altitude data and the real-air thermodynamic data used are reliable for application to this range of altitudes. Tabulated values at each altitude as a function of the temperature behind the the shock are presented to show the variation of the normal-shock parameters with flight Mach number and altitude, and some discussion of the dependence of the parameters on the initial pressure and temperature is given. A method for adapting the data to the case of oblique shocks is included.
Author: International Association of Geochemistry and Cosmochemistry
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 324
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Author: K. A. Wienert
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 228
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Book Description
