Calculations of Air Chemistry in the Electron-beam Heated Hypersonic Wind Tunnel PDF Download
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Author: C. C. Limbaugh
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: C. C. Limbaugh
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: C. C. Limbaugh
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: S. L. Petrie
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 40
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 384
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Book Description
Author: Defense Documentation Center (U.S.)
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 1032
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Book Description
Author: Wilbur C. Nelson
Publisher: Elsevier
ISBN: 1483223310
Category : Science
Languages : en
Pages : 801
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Book Description
The High Temperature Aspects of Hypersonic Flow is a record of the proceedings of the AGARD-NATO Specialists' Meeting, held at the Technical Centre for Experimental Aerodynamics, Rhode-Saint-Genese, Belgium in April 1962. The book contains the papers presented during the meeting that tackled a broad range of topics in the aspects of hypersonic flow. The subjects covered during the meeting include pressure measurements, interference effects, the use of wind tunnels in aircraft development testing, high temperature gas characteristics, boundary layer research, stability and control and the use of rocket vehicles in flight research. Aerospace engineers and aeronautical engineers will find the book invaluable.
Author: Donald J. Harney
Publisher:
ISBN:
Category : Chemical kinetics
Languages : en
Pages : 32
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 694
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Book Description
Author: Wayne Douglas Erickson
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 190
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Book Description
Author: Richard L. Humphrey
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 52
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Book Description
The one-dimensional flow equation for mass flow through the throat of a supersonic nozzle has been modified for use with real gas values of gamma and compressibility. Curve fits for gamma and Z and a simple iteration scheme have been developed for use with air and nitrogen over a temperature range of 300 to 6000 deg. K and a pressure of 10 to 100 atm. With this approach the sonic throat method can be used with the most recent gas tables to determine high temperature wind tunnel supply temperatures or enthalpies. (Author).
