Pressure Distribution on a Flat-bottom Canted Nose Half-cone Reentry Configuration at a Mach Number of 6.0
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Page : 28 pages
File Size : 50,36 MB
Release : 1962
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Page : 28 pages
File Size : 50,36 MB
Release : 1962
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Author : William O. Armstrong
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Page : 44 pages
File Size : 11,17 MB
Release : 1962
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Author : J. S. Hahn
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Page : 262 pages
File Size : 11,57 MB
Release : 1972
Category : Ablation (Aerothermodynamics)
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Page : 32 pages
File Size : 33,88 MB
Release : 1963
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Author : Warren A. Lawson
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Page : 64 pages
File Size : 13,64 MB
Release : 1960
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Author : R. R. Eaton
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Page : 60 pages
File Size : 46,53 MB
Release : 1968
Category : Aerodynamic load
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Author : James L. Amick
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Page : 52 pages
File Size : 30,6 MB
Release : 1961
Category : Fluid mechanics
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Author : Raul Jorge Conti
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Page : 38 pages
File Size : 17,68 MB
Release : 1961
Category : Heat
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Two circulation conical configurations having 15° half-angles were tested in laminar boundary layer at a Mach number of 6 and angles of attack up to 90°. One cone had a sharp nose and a fineness ratio of 1.87 and the other had a spherically blunted nose with a bluntness ratio of 0.1428 and a fineness ratio of 1.66. Pressure measurements and schlieren pictures of the flow showed that near-conical flow existed above 70° high pressure areas were present near the base and the bow shock wave was considerably curved.
Author : Dal V. Maddalon
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Page : 42 pages
File Size : 34,13 MB
Release : 1966
Category : Cone
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Page : 60 pages
File Size : 30,76 MB
Release : 1963
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