Heat-transfer and Pressure Measurements on a Concave-nose Cylinder for Mach Number Range of 2.49 to 4.44
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Page : 26 pages
File Size : 43,80 MB
Release : 1959
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Page : 26 pages
File Size : 43,80 MB
Release : 1959
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Author : J. Thomas Markley
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Page : 24 pages
File Size : 29,84 MB
Release : 1958
Category : Heat
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Abstract: The concave-nose stagnation-point heating is 40 percent of that of a hemisphere nose shape having the same diameter. At angles of attack of ℗±5© and ℗± 10© there is no increase in heating of the nose. Total pressures behind the shock were experienced up to 60© on the concave part for all angles of attack. The tests were made under sea-level conditions for a Reynolds number per foot of about 14 x 106.
Author : Richard D. Wagner
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Page : 44 pages
File Size : 30,64 MB
Release : 1961
Category : Fluid mechanics
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Author : Joseph Adams Shortal
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Page : 808 pages
File Size : 25,33 MB
Release : 1978
Category : Aeronautics
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Author : William E. Stoney
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Page : 38 pages
File Size : 28,64 MB
Release : 1958
Category : Cylinders
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Flat-faced cylinders of 12-inch dtameter and 4-inch diameter were tested at a Mach number of 2 and sea-level conditions in the preflight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. Both pressure distributions and heat-transfer rates were measured.
Author : William E. Stoney
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Page : 16 pages
File Size : 40,26 MB
Release : 1957
Category : Aerodynamic heating
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Author : Philip E. Everhart
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Page : 66 pages
File Size : 19,75 MB
Release : 1961
Category : Aerodynamic load
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Author : Morton Cooper
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Page : 19 pages
File Size : 23,35 MB
Release : 1958
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Author : Thorval Tendeland
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Page : 24 pages
File Size : 34,90 MB
Release : 1959
Category : Aerodynamic heating
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Page : 904 pages
File Size : 19,78 MB
Release : 1958
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