Experimental Convective Heat Transfer to a 4-inch and 6-inch Hemisphere at Mach Numbers from 1.62 to 3.04 PDF Download

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Experimental Convective Heat Transfer to a 4-inch and 6-inch Hemisphere at Mach Numbers from 1.62 to 3.04

Experimental Convective Heat Transfer to a 4-inch and 6-inch Hemisphere at Mach Numbers from 1.62 to 3.04 PDF Author: Leo T. Chauvin
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24

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Book Description
Abstract: Equilibrium temperatures and heat-transfer coefficients for a hemispherical nose have been measured for Mach numbers from 1.62 to 3.04. Heat transfer to the surface of the hemisphere was presented as Stanton number against Reynolds number for various surface heating conditions. Heat transfer at the stagnation point has been measured and correlated with theory. Transition from a laminar to a turbulent boundary layer was obtained at Reynolds numbers of approximately 1 x 106 corresponding to a region on the body located between 45© and 60© from the stagnation point.

Experimental Convective Heat Transfer to a 4-inch and 6-inch Hemisphere at Mach Numbers from 1.62 to 3.04

Experimental Convective Heat Transfer to a 4-inch and 6-inch Hemisphere at Mach Numbers from 1.62 to 3.04 PDF Author: Leo T. Chauvin
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24

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Book Description
Abstract: Equilibrium temperatures and heat-transfer coefficients for a hemispherical nose have been measured for Mach numbers from 1.62 to 3.04. Heat transfer to the surface of the hemisphere was presented as Stanton number against Reynolds number for various surface heating conditions. Heat transfer at the stagnation point has been measured and correlated with theory. Transition from a laminar to a turbulent boundary layer was obtained at Reynolds numbers of approximately 1 x 106 corresponding to a region on the body located between 45© and 60© from the stagnation point.

Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106

Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106 PDF Author: James R. Hall
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 34

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Book Description

Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8

Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 PDF 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.

Experimental Investigation of Heat-transfer Distributions in Deep Cavities in Hypersonic Separated Flow

Experimental Investigation of Heat-transfer Distributions in Deep Cavities in Hypersonic Separated Flow PDF Author: Allan R. Wieting
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 36

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Book Description
Hypervelocity wind tunnel tests to determine local cold wall convective heating rates to small rectangular cavities,

An Experimental and Numerical Study of Steady Forced-convection Heat Transfer in a Spherical Annulus

An Experimental and Numerical Study of Steady Forced-convection Heat Transfer in a Spherical Annulus PDF Author: Dean Byard Tuft
Publisher:
ISBN:
Category :
Languages : en
Pages : 242

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Book Description

Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9

Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 PDF Author: Charles B. Rumsey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 42

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Book Description
Abstract: Aerodynamic heat-transfer measurements were at six stations on the 40-inch-long 10° total-angle conical nose of a rocket-propelled model which was flight tested at Mach numbers up to 5.9. The range of local Reynolds number was from 6.6 x 106 to 55.2 x 106. Laminar, transitional, and turbulent heat-transfer coefficients were measured, and, in general, the laminar and turbulent measurements were in good agreement with theory for cones. Experimental transition Reynolds numbers varied from less than 8.5 x 106 to 19.4 x 106. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 106 to 19.4 x 106 as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperatures.

Variation in Heat Transfer During Transient Heation of a Hemisphere at a Mach Numer of 2

Variation in Heat Transfer During Transient Heation of a Hemisphere at a Mach Numer of 2 PDF Author: Roland D. English
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 30

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Book Description

Experimental Investigation of Free-convection Heat Transfer in Vertical Tube at Large Grashof Numbers

Experimental Investigation of Free-convection Heat Transfer in Vertical Tube at Large Grashof Numbers PDF Author: E. R. G. Eckert
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 42

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Book Description

Laminar Heat-transfer Distributions for a Blunted-cone, Cone-frustum Reentry Configuration at Mach 10

Laminar Heat-transfer Distributions for a Blunted-cone, Cone-frustum Reentry Configuration at Mach 10 PDF Author: J. David Dearing
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 28

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Book Description

Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration

Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration PDF Author: Charles B. Rumsey
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 26

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Book Description
Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.