Investigation of Helicopter Rotor Blade Flutter and Flapwise Bending Response in Hovering

Investigation of Helicopter Rotor Blade Flutter and Flapwise Bending Response in Hovering PDF Author: Frank A. DuWaldt
Publisher:
ISBN:
Category : Flutter (Aerodynamics)
Languages : en
Pages : 326

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Investigation of Helicopter Rotor Blade Flutter and Flapwise Bending Response in Hovering

Investigation of Helicopter Rotor Blade Flutter and Flapwise Bending Response in Hovering PDF Author: Frank A. DuWaldt
Publisher:
ISBN:
Category : Flutter (Aerodynamics)
Languages : en
Pages : 326

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Technical Note - National Advisory Committee for Aeronautics

Technical Note - National Advisory Committee for Aeronautics PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1142

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Technical Note

Technical Note PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 732

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NASA Technical Note

NASA Technical Note PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1196

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Report

Report PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 900

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Analysis and Comparison with Theory of Flow-field Measurements Near a Lifting Rotor in the Langley Full-scale Tunnel

Analysis and Comparison with Theory of Flow-field Measurements Near a Lifting Rotor in the Langley Full-scale Tunnel PDF Author: Harry H. Heyson
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 696

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Results of an investigation in the Langley full-scale tunnel of the induced flow near a lifting rotor are given. Measurements of stream angles and velocities were made in several transverse planes along and behind the rotor in four different conditions representative of the cruising and high-speed ranges of flight. These measurements indicate that available theory may be used to calculate with reasonable accuracy the induced flow over the forward three-quarters of the disk for these flight conditions provided that a realistic nonuniform rotor disk-load distribution is assumed. Rearward of the three-quarter-diameter point, calculations of the induced velocity are increasingly inaccurate due to the rolling up of the trailing-vortex system. Farther rearward, well behind the rotor, the flow may be represented more accurately by the flow behind a uniformly loaded wing.

Report

Report PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 100

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Index of NACA Technical Publications

Index of NACA Technical Publications PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580

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Current Papers

Current Papers PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 46

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Applied Mechanics Reviews

Applied Mechanics Reviews PDF Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 616

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