Experimental Investigation of Temperature Recovery Factors on Bodies of Revolution at Supersonic Speeds

Experimental Investigation of Temperature Recovery Factors on Bodies of Revolution at Supersonic Speeds PDF

Author: William R. Wimbrow

Publisher:

Published: 1949

Total Pages: 26

ISBN-13:

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Local temperature recovery factors have been measured on two bodies of revolution at Mach numbers of 2.0 and are shown to be independent of Mach number, Reynolds number, or body shape. The measured recovery factor is well represented by the square root of Prandtl number for laminar boundary layers and by the cube root of Prandtl number for turbulent boundary layers, as predicted by theory.

Experimental Investigation of Flutter of a Propeller with Clark Y Section Operating at Zero Forward Velocity at Positive and Negative Blade-angle Settings

Experimental Investigation of Flutter of a Propeller with Clark Y Section Operating at Zero Forward Velocity at Positive and Negative Blade-angle Settings PDF

Author: John E. Baker

Publisher:

Published: 1949

Total Pages: 686

ISBN-13:

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The highest flutter speeds were found in the vicinity of the angle of zero aerodynamic moment and the flutter speed increased considerably in this region with decreasing pressure. Over the rest of the pitch range, the flutter speeds were much lower and varied little with pressure.

Report

Report PDF

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1951

Total Pages: 30

ISBN-13:

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Two-dimensional Flow on General Surfaces of Revolution in Turbomachines

Two-dimensional Flow on General Surfaces of Revolution in Turbomachines PDF

Author: John D. Stanitz

Publisher:

Published: 1952

Total Pages: 734

ISBN-13:

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A method of analysis is developed for two dimensional flow on general surfaces of revolution in turbomachines with arbitrary blade shapes. The method of analysis is developed for steady, compressible, nonviscous, irrotational flow that is assumed uniform normal to the surfaces of revolution. Incompressible solutions on a mean surface of revolution between the hub and shroud are presented for four rates through each of two centrifugal impellers with the same hub-shroud contours but with different blade spacings. In addition, correlation equations are developed whereby the velocity components and the stream function distribution can be predicted for compressible or incompressible flow in straight-blade impellers only, with any tip speed, flow rate, area variation, blade spacing, and for any flow surface of revolution.

Charts for Estimating Rotor-blade Flapping Motion of High-performance Helicopters

Charts for Estimating Rotor-blade Flapping Motion of High-performance Helicopters PDF

Author: Robert J. Tapscott

Publisher:

Published: 1956

Total Pages: 692

ISBN-13:

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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.

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