Local Leading Edge Heat Transfer on a Flat Plate in Rarefied Hypersonic Flow PDF Download
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Author: James David Hendry
Publisher:
ISBN:
Category :
Languages : en
Pages : 80
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Book Description
The local heat flux to a sharp edged flat plate was measured over the range 32.8
Author: James David Hendry
Publisher:
ISBN:
Category :
Languages : en
Pages : 80
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Book Description
The local heat flux to a sharp edged flat plate was measured over the range 32.8
Author: Henry T. Nagamatsu
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 68
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Book Description
Author: K. S. Heffner
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
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Book Description
Author: H. T. Nagamatsu
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
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Book Description
An investigation was conducted in a hypersonic shock tunnel to determine the local heat transfer rates for a sharp leading edge flat plate. The free stream Mach number range was 7.95 to 25.l with stagnation temperatures of approximately 2550 and 6500 R. For these temperature and Mach number conditions, the strong interaction parameter varied from 2.35 to 826. The corresponding Knudsen numbers, based on the ratio of the free stream mean free path and the leading edge thickness, varied from 0.38 to 85.5. The sputtered platinum heat gages were dynamically calibrated by passing a moderate strength shock wave across the gages and observing the change in resistance due to a step function temperature rise. By this method the gage characteristics were determined for the same pressure rises encountered in the test section.
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: William Whyte Joss
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 7
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 834
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1964
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Book Description
Author: H. T. NAGAMATSU
Publisher:
ISBN:
Category :
Languages : en
Pages : 39
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Book Description
An investigation was conducted in a hypersonic shock tunnel to determine the induced pressures and the local heat transfer rates for a flat plate with sharp leading edge. The free stream Mach number range was 7.95 to 25.1 with stagnation temperatures of approximately 2300 and 7000 R. For these temperatures and Mach number conditions, the strong interaction parameter, varied from 2.35 to 826 and the corresponding Knudsen numbers, based on the ratio of the free stream mean free path and the leading edge thickness, varied from 0.4 to 86. For free stream Mach numbers greater than 10, Knudsen numbers of approximately unity, and perfect gas conditions, the observed experimental induced pressures varied as the square root of the strong interaction parameter and the local heat transfer rates varied as the cube root of the strong interaction parameter to the fourth power as predicted by the noninsulated flat plate theory of Li and Nagamatsu. When the Knudsen number and the Mach number are much greater than 1, the leading edge slip phenomenon drastically reduced both the induced pressures and local heat transfer rates as compared to the theoretical values predicted with no slip at the surface. Schlieren photographs indicate the presence of slip flow at the sharp leading edge in that the formation of the strong shock wave and the boundary layer was delayed. (Author).
