Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10 6 PDF Download

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Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10 6

Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10 6 PDF Author: James J. Buglia
Publisher:
ISBN:
Category :
Languages : en
Pages : 26

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Book Description

Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10 6

Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10 6 PDF Author: James J. Buglia
Publisher:
ISBN:
Category :
Languages : en
Pages : 26

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Book Description

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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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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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.

Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polishes 8-inc-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 10 6

Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polishes 8-inc-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 10 6 PDF Author: James R. Hall
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Book Description

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 10(exp

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 10(exp PDF Author: James R. Hall
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Aerodynamic Heating and Boundary-layer Transition on a 1/10-power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-stream Reynolds Numbers Up to 16 X 10(6)

Aerodynamic Heating and Boundary-layer Transition on a 1/10-power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-stream Reynolds Numbers Up to 16 X 10(6) PDF Author: Benjamine J. Garland
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36

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An Experimental Investigation of Boundary-layer Transition on a 10 ̊half-angle Cone at Mach 6.9

An Experimental Investigation of Boundary-layer Transition on a 10 ̊half-angle Cone at Mach 6.9 PDF 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.

Journal of the Royal Aeronautical Society

Journal of the Royal Aeronautical Society PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 962

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

Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 PDF Author: Charles B. Rumsey
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 38

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Book Description

Boundary-layer Transition on Cones Near Mach One in an Aeroballistic Range

Boundary-layer Transition on Cones Near Mach One in an Aeroballistic Range PDF Author: J. Leith Potter
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 36

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Book Description
The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semiangle cones at slightly supersonic free-stream Mach numbers, 1.04 = or