An Experimental Investigation of Heat Transfer to Cones in Rarified Hypersonic Flow PDF Download
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Author: Carl T. Berry
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages :
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Book Description
Author: Carl T. Berry
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages :
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Book Description
Author: Carl T. Berry
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages :
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Author: Edward M. Schmidt
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Book Description
The paper presents the results of an experimental survey of the flow field around a sharp, 10 degree half angle cone. Tests were conducted at a free stream Mach number of 7.7 for a range of free stream Reynolds numbers of 110,000 to 171,000 per foot. Surface heat transfer data indicates that the cone boundary layer varies from laminar to fully developed turbulent over this Reynolds number range. The base pressure variation was also obtained throughout this range of Reynolds numbers; from this, the interrelation between the surface boundary layer properties and the base pressure is discussed. A series of tests were conducted in the near wake region at two different values of free stream Reynolds number, i.e., 330,000 and 1,650,000 per foot, corresponding to a completely laminar and fully developed turbulent surface boundary layer at the cone shoulder, respectively. The relationship between boundary layer properties and near wake properties is studied. (Author).
Author: Carl T. Berry
Publisher:
ISBN:
Category :
Languages : en
Pages : 99
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Book Description
The present study was an experimental investigation of the laminar surface heat transfer distribution about cones. The study was conducted in the Princeton University hypersonic nitrogen facility and covered a wide range of geometries and test conditions in an attempt to evaluate the numerical accuracy, theoretical modeling, and range of applicability of the several theories which are available. Cones, varying from 3 degrees to 30 degrees, with two nose bluntnesses, and lengths from one to eight inches were examined over a range of test conditions: Mach numbers from 16 to 25, and unit Reynolds numbers from 7,000 to 40,000 per inch. The detailed heat transfer distributions, covering the full range of 'nose dominated', 'merged', and 'weak interaction' regimes, were compared with several theoretical prediction techniques. A critical review of the modeling involved in the theories, as compared to the experiments, is presented. (Author).
Author: Marvin I. Kussoy
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
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Book Description
Drag, heat transfer, and number flux were measured on sharp cones in the near free, molecule flow regime, and the results were compared with available Monte Carlo calculations. In general, the calculations predicted the magnitude of the data; however, the heat transfer and drag increased with increasing Knudsen number at a faster rate than predicted. Also the drag coefficients measured for the slender cones at high Knudsen number were higher than predicted for free molecule flow. These disagreements between theory and experiment could possibly be attributed to the simplicity of the surface interaction laws assumed in the theory. Reynolds analogy factors obtained from the experimental measurements agreed with free-molecule values and also with that obtained by the Monte Carlo technique.
Author: Walter Samuel Bradfield
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 344
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Author: Michael C. Fischer
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 76
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Book Description
Boundary layer transition on nose cones at hypersonic speeds.
Author: Reginald M Machell
Publisher: Hassell Street Press
ISBN: 9781013398810
Category :
Languages : en
Pages : 130
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Book Description
This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Author: Reginald M. Machell
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 0
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Author: Yu V. Nikolskii
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Book Description
The research sheds light on heat transfer in spheres and thin cones at a zero angle of attack. The investigations were conducted in a vacuum wind tunnel at Mach numbers M = 4.9-9.5, and Reynold numbers Re0 = 35-1 for spheres, and Re0 = 100-4 for cones; this corresponds to the transition range between free-molecular flow and the flow of a continuous medium. The procedure used was the measurement of the total heat flow under standard conditions with compensation of heat losses in a sting, and an independent measurement of the radiant heat flux. A comparison of the data with the results of the theoretical calculation was made.
