Experimental Investigation of Temperature Recovery Factors on a 10 [degrees] Cone at Angle of Attack at a Mach Number of 3.12 PDF Download
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Author: John R. Jack
Publisher:
ISBN:
Category :
Languages : en
Pages : 15
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![Experimental Investigation of Temperature Recovery Factors on a 10 [degrees] Cone at Angle of Attack at a Mach Number of 3.12 PDF](https://books.google.com/books/content/images/frontcover/cBLotgAACAAJ?fife=w80-h100)
Author: John R. Jack
Publisher:
ISBN:
Category :
Languages : en
Pages : 15
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Book Description
Author: John R. Jack
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 15
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Book Description
For the windward surface of the model, local recovery factors in the fully laminar and turbulent regions were not significantly affected by changes in angle of attack. At all angles of attack, increasing the free-stream Reynolds number moved the transition region upstream. For a given angle of attack, the transition region on the leeward surface is substantially upstream of that on the windward surface.
Author: John O. Reller
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 64
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Book Description
Abstract: Temperature recovery factors were determined for a slender, thin-walled cone-cylinder, having a 12° vertex angle and a 1.25-inch-diameter cylinder, at Mach numbers from 3.02 to 6.30. The angle-of-attack range was 0° to 45° at Mach numbers up to 3.50, and about 0° to 20° at Mach numbers from 4.23 to 6.30. A transverse cylinder of the same diameter was also tested at Mach number 3.02. Free-stream Reynolds numbers varied from 1.8 to 11.0 million per foot. Flow visualization studies of boundary-layer transition and flow separation were made and the results correlated with recovery-factor measurements.
Author: Michael C. Fischer
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 76
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Boundary layer transition on nose cones at hypersonic speeds.
Author: Howard A. Stine
Publisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 20
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A turbulent-boundary-layer temperature recovery factor f 0.885 plus or minus 0.011 was measured on both a 10 degree cone and a 40 degree cone cylinder at Mach numbers from 2 to 3.8 and Reynolds numbers based on surface kinematic viscosity from 400,000 to 4,000,000. Comparisons are made with available theories and experiments.
Author: Frank A. Pfyl
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 66
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Author: Jerome D. Julius
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 32
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 72
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Author: Alfred Merle Morrison
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 102
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Book Description
A series of one-degree-of-freedom dynamic wind tunnel measurements were made for a standard Supersonic Tunnel Association ten degree cone with varying bluntnesses of .25, .1, .0167, and .07. Variations of the stability coefficients with angle-of-attack, bluntness, Reynolds number, and Mach number are obtained including Mach 18 data points for which no previous data existed. An explanation of reported difference between measured dynamic stability as obtained from ballistic range and wind tunnel techniques is offered. The equations of motion, data reduction techniques and experimental methods are also developed.
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.
