An Investigation of Laminar Heat Transfer to Slender Cones in the Hypersonic Shock Tunnel PDF Download
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Author: Charles E. Wittliff
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82
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Book Description
Author: Charles E. Wittliff
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82
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Book Description
Author: Davis H. Crawford
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 680
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Book Description
At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
Author: Paul K. Chang
Publisher:
ISBN:
Category :
Languages : en
Pages : 133
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Book Description
The problems of aerodynamic and heat transfer characteristics of slender sharp nosed hypersonic cones over a wide range of angles of attack are examined and the analytical solutions are presented. Three particular problems are studied: (1) inviscid flow characteristics of shock layer involving laminar separation in the leeward side with undisturbed free stream Mach number 7.95 and angle of attack 20 degrees for cone half angle 10 degrees, (2) attached three-dimensional compressible boundary layer over the cone, (3) aerodynamic and heat transfer characteristics of turbulent separated flow. (Author).
Author: David E. Boylan
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 68
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Book Description
The report presents heat-transfer-rate measurements on sharp and blunt 10-deg half-angle cones at angles of attack between -9 and +10 deg in a low-density, hypersonic wind tunnel. Circumferential and longitudinal distributions are presented for cold wall conditions for a range at Mach and Reynolds numbers. The effect of source-like flows was studied by utilizing both conical and contoured expansion nozzles with the same free-stream similarity parameters and model wall temperatures. Comparisons are made with previously published experimental and theoretical results. (Author).
Author: B. J. Griffith
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 44
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Book Description
Author: Donald M. Wilson
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 94
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Book Description
Turbulent boundary layer heat transfer rates were measured on a thin-walled slender cone at a free-stream Mach number of 5.0. Wall to stagnation temperature ratios from 0.15 to 0.40 were obtained by pre-cooling the model using liquid nitrogen. Tests at a wide range of Reynolds numbers were conducted by varying the tunnel supply pressure; thus providing data for both laminar and mixed laminar-turbulent types of boundary layers. The experimental results obtained were compared with existing theories which predict convective heat transfer coefficients. These comparisons indicate that the data corresponding to a 760R supply temperature verify the predictions of Winkler and Cha; however, data acquired at a supply temperature of 1160R substantiate the predictions of Spalding and Chi. (Author).
Author: W. Carson Lyons
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 284
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Book Description
Author: David B. Wilkinson
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 154
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Book Description
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: Raul Jorge Conti
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 38
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Book Description
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.
