An Experimental Investigation of Laminar Heat Transfer to Cones at Hypersonic Speeds PDF Download
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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: 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: Carl T. Berry
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages :
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Author: Carl T. Berry
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages :
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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: Lionel Pasiuk
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 72
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Book Description
Theoretical laminar heat transfer rates to a sphere-cone model at angles of yaw up to 18 degrees are compared with wind tunnel data measured at Mach numbers of 3.2 and 4.8. Two methods of heat transfer prediction have been chosen--the methods of Beckwith and VaglioLaurin. These require that the inviscid streamline pattern on the surface of the yawed spherecone model be known. These steamlines have been calculated from measured surface pressure distributions. The theory of Beckwith agrees reasonably well with the experimental data.
Author: Raul Jorge Conti
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 38
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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: Charles E. Wittliff
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82
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Author: Robert H. Feldhuhn
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 148
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Book Description
Pressure, heat transfer, force, flow field surveys and flow visualization measurements on an inclined cone were obtained in a wind tunnel at a nominal Mach number of 6. Force measurements were also obtained for a 2/3 power law body and two ducted-cone configurations.
Author: Kenneth M. Nicoll
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
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An experimental investigation was made of the recovery factor and heat-transfer distributions on a set of cone-models incorporating annular cavities. This study is the second part of a two-part program. The first section contained measurements of the pressure distributions. The results show that the recovery factor in laminar, hypersonic cavity flow is almost constant within the cavity and downstream of reattachment, and is very close to the laminar attached-flow value. In the immediate vicinity of reattachment, the recovery factor is slightly higher than this value (less than 5%). The lowest values of the heat-transfer coefficient are found on the cavity floors, where a minimum of about 10 to 20% of the attached-flow value is reached. The highest values of the heat-transfer coefficient are in the immediate vicinity of reattachment. An average reattachment heattransfer coefficient of about three times the basic cone heat-transfer coefficient was measured on one cavity model. (Author).
Author: Walter Samuel Bradfield
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 344
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