Experimental Study of Effects of Geometric Variables on Performance of Contoured Rocket Engine Exhaust Nozzles PDF Download
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Author: Harry E. Bloomer
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ISBN:
Category : Liquid fuels
Languages : en
Pages : 32
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Author: Harry E. Bloomer
Publisher:
ISBN:
Category : Liquid fuels
Languages : en
Pages : 32
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Author: Harry E. Bloomer
Publisher:
ISBN:
Category : Liquid propellant rockets
Languages : en
Pages : 66
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Author: Harry E. Bloomer
Publisher:
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Category :
Languages : en
Pages : 27
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Author: Harry E. Bloomer
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Category :
Languages : en
Pages : 61
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An investigation was conducted to determine the performance and flow separation characteristics of a family of conical rocket exhaust nozzles. The nozzles were mounted on a water-cooled JP-4 gaseous-oxygen thrust chamber with a 2.67-inchdiameter throat. The range of nozzle variables included divergent half-angles from 15 to 30 degrees nozzle area ratios from 8/1 to 75/1, and pressure ratios from 35 to 840. The results of the investigation showed that, for nozzles of equal length, the 20 or 25 degrees half-angles were superior at vacuum conditions. The advantage of these over the smaller area ratio, 15 degrees half-angle nozzles amounted to about 1% in thrust coefficient. Nozzle separation characteristics were generalized by the use of the Mach number ratio across the oblique shock wave which occurs at the separation point. (Author).
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Category :
Languages : en
Pages : 390
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Author:
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Category : Science
Languages : en
Pages : 44
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Category : Government publications
Languages : en
Pages : 1990
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Author: United States. Superintendent of Documents
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Category : United States
Languages : en
Pages : 1504
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Author: United States. Superintendent of Documents
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Category : Government publications
Languages : en
Pages : 1284
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Category : Outer space
Languages : en
Pages : 544
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A Chinese boy's greatest wish is to be an artist but he is too poor to buy a good brush until a wizard appears and gives him one with magic powers.
