Author: Mitchel H. Bertram
Publisher:
ISBN:
Category : Gas flow
Languages : en
Pages : 80
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Book Description
An analytic investigation was made to show the extent of correlation of the exact oblique shock parameters that may be accomplished by means of similarity parameters suggested by approximate theory. The exact theory for the inviscid flow of a perfect gas was calculated for Mach numbers of 1.1 to 40, ratios of specific heats from 1 to 5/3, and angles of attack from 0° to shock detachment. From consideration of the approximate theory and the concept of effective ratio of specific heats, the oblique shock correlations were found to be useful for the rapid calculation of many flow parameters for an equilibrium real gas. Some useful correlations are also given for the case of isentropic expansion around a sharp corner.
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 830
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Author: C. F. Ehrlich
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 564
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Author:
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ISBN:
Category : Government publications
Languages : en
Pages : 1284
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 364
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Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1496
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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: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1248
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Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : United States
Languages : en
Pages : 1250
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Author: John S. Dennard
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 168
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Book Description
Oblique-shock tables are presented for air with initial Mach numbers from 1.05 to 12.0 and flow-deflection angles from 0 degrees up to the maximum turning angle for attached flow. Parameters presented are flow-deflection angle, shock-wave angle, total-pressure ratio, static-pressure, density, and temperature ratios, downstream Mach number, ratio of downstream velocity to maximum velocity, and increase in entropy. Perfect-gas equations have been used throughout these calculations.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 966
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