Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45° PDF Download

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Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45°

Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45° PDF 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.

Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45°

Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45° PDF 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.

Temperature Recovery Factors on a Slender 12 Degree Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45 Degrees

Temperature Recovery Factors on a Slender 12 Degree Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45 Degrees PDF Author: John O. Jr Reller
Publisher:
ISBN:
Category :
Languages : en
Pages : 56

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Temperature Recovery Factors on a 40-Degree Cone Cylinder with Turbulent Boundary Layer at Mach Numbers 4.1 and 4.8

Temperature Recovery Factors on a 40-Degree Cone Cylinder with Turbulent Boundary Layer at Mach Numbers 4.1 and 4.8 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95

Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95 PDF Author: Jerome D. Julius
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 32

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Book Description

Temperature Recovery Factors in the Transitional and Turbulent Boundary Layer on a 40-Degree Cone Cylinder at Mach Number 2.9

Temperature Recovery Factors in the Transitional and Turbulent Boundary Layer on a 40-Degree Cone Cylinder at Mach Number 2.9 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 64

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Book Description
Temperature recovery factors were determined on the cylindrical surface of a number of 40 deg cone cylinder models at zero angle of attack and at M = 2.86. The investigation was performed in a 40- by 40-cm intermittent tunnel and an 18- by 18-cm continous tunnel. With atmospheric tunnel-supply conditions, the turbulent recovery factor was found to be 0.89 + or - 0.5% and independent of Reynolds number in the range of 200,000 to 800,000, with Reynolds number based on wall conditions. The turbulent recovery factor can be represented by the cube root of the Prandtl number for a Prandtl number calculated at wall conditions. In the transitional region of the boundary layer, a maximum recovery factor 0.5 to 1% higher than the turbulent value was obtained. Boundary layer history had a marked effect on the value of the recovery factor. The results were compared with the theoretical and experimental findings of other investigators.

A Review of High-speed, Convective, Heat-transfer Computation Methods

A Review of High-speed, Convective, Heat-transfer Computation Methods PDF Author: Michael E. Tauber
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44

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Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 80

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Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90°

Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90° PDF 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.

Experimental Investigation of Temperature Recovery Factors on a 10 [degrees] Cone at Angle of Attack at a Mach Number of 3.12

Experimental Investigation of Temperature Recovery Factors on a 10 [degrees] Cone at Angle of Attack at a Mach Number of 3.12 PDF Author: John R. Jack
Publisher:
ISBN:
Category :
Languages : en
Pages : 15

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Book Description

Experimental Investigation of Temperature Recovery Factors on a 10 Degree Cone at Angle of Attack at a Mach Number of 3.12

Experimental Investigation of Temperature Recovery Factors on a 10 Degree Cone at Angle of Attack at a Mach Number of 3.12 PDF 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.