Heat-transfer Measurements on a Low-fineness-ratio Cylinder at a Mach Number of 10.4 and Angles of Attack from 0° to 90° PDF Download

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Heat-transfer Measurements on a Low-fineness-ratio Cylinder at a Mach Number of 10.4 and Angles of Attack from 0° to 90°

Heat-transfer Measurements on a Low-fineness-ratio Cylinder at a Mach Number of 10.4 and Angles of Attack from 0° to 90° PDF Author: Philip E. Everhart
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44

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Book Description

Heat-transfer Measurements on a Low-fineness-ratio Cylinder at a Mach Number of 10.4 and Angles of Attack from 0° to 90°

Heat-transfer Measurements on a Low-fineness-ratio Cylinder at a Mach Number of 10.4 and Angles of Attack from 0° to 90° PDF Author: Philip E. Everhart
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44

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Book Description

Heat Transfer Measurements on a Low-fineness- Ratio Cylinder at a Mach Number of 10.4 and Angles of Attack from 0 Deg to 90 Deg

Heat Transfer Measurements on a Low-fineness- Ratio Cylinder at a Mach Number of 10.4 and Angles of Attack from 0 Deg to 90 Deg PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 50

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Book Description

Heat-transfer Measurements on a Low-fineness-ratio Cylinder at a Mach Number of 10.4 and Angles of Attack from 0° to 90°

Heat-transfer Measurements on a Low-fineness-ratio Cylinder at a Mach Number of 10.4 and Angles of Attack from 0° to 90° PDF Author: Philip E. Everhart
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32

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Book Description

Heat Transfer to the Windward Side of a Fineness-ratio-2.9 Cylinder with Nearly Spherical Ends at a Mach Number of 6 and Angles of Attack of 50, ̊ 70, ̊ and 90

Heat Transfer to the Windward Side of a Fineness-ratio-2.9 Cylinder with Nearly Spherical Ends at a Mach Number of 6 and Angles of Attack of 50, ̊ 70, ̊ and 90 PDF Author: James Larry Hunt
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 50

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Book Description

Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 256

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Book Description

Heat-Transfer and Pressure Measurements on a Flat-Face Cylinder at a Mach Number Range of 2.49 to 4.44

Heat-Transfer and Pressure Measurements on a Flat-Face Cylinder at a Mach Number Range of 2.49 to 4.44 PDF Author: Paige B. Burbank
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 30

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Book Description

Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7

Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 PDF Author: Charles R. Rumsey
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 66

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Book Description

Heat Transfer to the Windward Side of a Fineness-ratio-2.9 Cylinder with Nearly Spherical Ends at a Mach Number of 6 and Angles of Attack of 50°, 70°, and 90°

Heat Transfer to the Windward Side of a Fineness-ratio-2.9 Cylinder with Nearly Spherical Ends at a Mach Number of 6 and Angles of Attack of 50°, 70°, and 90° PDF Author: James L. Hunt
Publisher:
ISBN:
Category :
Languages : en
Pages : 44

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Book Description

Heat Transfer to Bodies at Angles of Attack

Heat Transfer to Bodies at Angles of Attack PDF Author: William V. Feller
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 14

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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.