Determination of Inflow Through Helicopter Rotor Disc in Forward Flight PDF Download
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Author: Douglas Michel
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
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Author: Douglas Michel
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
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Book Description
Author: Gaetano Falabella
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages : 184
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Book Description
Inflow distributions, azimuth and spanwise, were determined analytically from measured pressure distributions and blade-motion data on a model helicopter rotor blade under hovering and simulated forward-flight conditions. Pressures and corresponding blade flapping were recorded for various rotor conditions at tip-speed ratios of 0.10 to 1.00. Included in this range are one-bladed-rotor operation effects, deliberate blade stall, data on the effects of cyclic pitch, and tests on a rotor with 13-percent-offset flapping hinge. Since the offset-flapping-hinge rotor was used primarily as a means of alleviating stall in order to obtain inflow data at high-tip-speed rations (mu) in the vicinity of 1.0, no cyclic pitch was used to balance out the hub moments resulting from the incorporation of offset hinges. It is these moments which are the primary source of the stall alleviation.
Author: Gaetano Falabella
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 174
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Book Description
Author: John C. Wilson
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages : 60
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Book Description
Author: Wayne Johnson
Publisher: Cambridge University Press
ISBN: 1107355281
Category : Technology & Engineering
Languages : en
Pages : 949
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Book Description
A rotorcraft is a class of aircraft that uses large-diameter rotating wings to accomplish efficient vertical take-off and landing. The class encompasses helicopters of numerous configurations (single main rotor and tail rotor, tandem rotors, coaxial rotors), tilting proprotor aircraft, compound helicopters, and many other innovative configuration concepts. Aeromechanics covers much of what the rotorcraft engineer needs: performance, loads, vibration, stability, flight dynamics, and noise. These topics include many of the key performance attributes and the often-encountered problems in rotorcraft designs. This comprehensive book presents, in depth, what engineers need to know about modelling rotorcraft aeromechanics. The focus is on analysis, and calculated results are presented to illustrate analysis characteristics and rotor behaviour. The first third of the book is an introduction to rotorcraft aerodynamics, blade motion, and performance. The remainder of the book covers advanced topics in rotary wing aerodynamics and dynamics.
Author: Gabriel Boehler
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 56
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 510
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Author: T. A. Egolf
Publisher:
ISBN:
Category :
Languages : en
Pages : 228
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Book Description
An analytic investigation to generalize wake geometry of a helicopter rotor in steady level forward flight and to demonstrate the influence of wake deformation in the prediction of rotor airloads and performance is described. Volume 1 presents a first level generalized wake model based on theoretically predicted tip vortex geometries for a selected representative blade design. The tip vortex distortions are generalized in equation form as displacements from the classical undistorted tip vortex geometry in terms of vortex age, blade azimuth, rotor advance ratio, thrust coefficient, and number of blades. These equations were programmed to provide distorted wake coordinates at very low cost for use in rotor airflow and airloads prediction analyses. The sensitivity of predicted rotor airloads, performance, and blade bending moments to the modeling of the tip vortex distortion are demonstrated for low to moderately high advance ratios for a representative rotor and the H-34 rotor. Comparisons with H-34 rotor test data demonstrate the effects of the classical, predicted distorted, and the newly developed generalized wake models on airloads and blade bending moments. Use of distorted wake models results in the occurrence of numerous blade-vortex interactions on the forward and lateral sides of the rotor disk. The significance of these interactions is related to the number and degree of proximity to the blades of the tip vortices. The correlation obtained with the distorted wake models (generalized and predicted) is encouraging.
Author: Peter Frederick Lorber
Publisher:
ISBN:
Category : Helicopters
Languages : en
Pages : 132
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Book Description
