Correlation of Supersonic Convective Heat-transfer Coefficients from Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10) PDF Download
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Author: Leo T. Chauvin
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 46
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Book Description
Heat transfer data are presented for a Mach number range of 1.02 to 2.48 and for a Reynolds number range of 3,180,000 to 163,850,000 based on the axial distance from the nose to the point at which temperature measurements were made.
Author: Leo T. Chauvin
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 46
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Book Description
Heat transfer data are presented for a Mach number range of 1.02 to 2.48 and for a Reynolds number range of 3,180,000 to 163,850,000 based on the axial distance from the nose to the point at which temperature measurements were made.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1136
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 500
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 424
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Book Description
Author: Max C. Kurbjun
Publisher:
ISBN:
Category : Noise
Languages : en
Pages : 742
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Book Description
Overall sound-pressure levels and frequency spectra of the noise emitted from a full-scale, 7.2-foot-diameter, 3, 500 rpm, three-blade, supersonic propeller mounted on a turbine-powered airplane have been obtained under static conditions at stations about the propeller at a 100-foot radius.
Author: Donald E. Coletti
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
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Book Description
Author: Morton Cooper
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 94
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 32
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Book Description
Author: Robert J. Tapscott
Publisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 692
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Book Description
Theoretically derived charts showing steady-state and first- and second-harmonic flapping coefficients are presented for helicopter rotors having hinged rectangular blades with a linear twist of 0, -8, and -16 degrees. The charts, showing the rotor flapping coefficients for combinations of inflow ratio and blade pitch angle, are presented for tip-speed ratios ranging from 0.05 to 0.50.
