An Experimental Study of Dynamic Stall on Advanced Airfoil Sections. Volume 1: Summary of the Experiment PDF Download
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 108
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Book Description
The static and dynamic characteristics of seven helicopter sections and a fixed-wing supercritical airfoil were investigated over a wide range of nominally two-dimensional flow conditions, at Mach numbers up to 0.30 and Reynolds numbers up to 4x10 to the 6th power. Details of the experiment, estimates of measurement accuracy, and test conditions are described in this volume. The results of the experiment show important differences between airfoils, which would otherwise tend to be masked by differences in wind tunnels, particularly in steady cases. All of the airfoils tested provide significant advantages over the conventional NACA 0012 profile. In general, however, the parameters of the unsteady motion appear to be more important than airfoil shape in determining the dynamic-stall airloads.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 108
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Book Description
The static and dynamic characteristics of seven helicopter sections and a fixed-wing supercritical airfoil were investigated over a wide range of nominally two-dimensional flow conditions, at Mach numbers up to 0.30 and Reynolds numbers up to 4x10 to the 6th power. Details of the experiment, estimates of measurement accuracy, and test conditions are described in this volume. The results of the experiment show important differences between airfoils, which would otherwise tend to be masked by differences in wind tunnels, particularly in steady cases. All of the airfoils tested provide significant advantages over the conventional NACA 0012 profile. In general, however, the parameters of the unsteady motion appear to be more important than airfoil shape in determining the dynamic-stall airloads.
Author: K. W. McAlister
Publisher:
ISBN:
Category :
Languages : en
Pages : 639
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 662
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 646
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Book Description
Experimentally derived force and moment data are presented for eight airfoil sections that were tested at fixed and varying incidence in a subsonic two-dimensional stream. Airfoil incidence was varied through sinusoidal oscillations in pitch over a wide range of amplitude and frequency. The surface pressure distribution, as well as the lift, drag, and pitching moment derived therefrom, are displayed in a uniform fashion to delineate the static and dynamic characteristics of each airfoil both in and out of stall. (Author).
Author:
Publisher:
ISBN:
Category : Stalling (Aerodynamics)
Languages : en
Pages :
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Book Description
The static and dynamic characteristics of seven helicopter sections and a fixed wing supercritical airfoil were investigated over a wide range of nominally two-dimensional flow conditions. The results of the experiment show important differences between airfoils, which would otherwise tend to be masked by differences in wind tunnels, particularly in steady cases. All of the airfoils tested provide significant advantages over the conventional NASA 0012 profile. However, the parameters of the unsteady motion appear to be more important than airfoil shape in determining the dynamic-stall airloads.
Author: Claude Béguier
Publisher: Montréal : École polytechnique de Montréal
ISBN:
Category :
Languages : en
Pages : 74
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Book Description
Author: Wyatt Spellman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 152
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Book Description
Author: Koji Isogai
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 19
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Book Description
Unsteady behavior of the reattachment point of a short bubble on a two-dimensional wing of NACA 0012 airfoil section during rapid change of angle of attack was studied by the use of miniature pressure transducers installed in the model for the purpose of detecting the sudden pressure rise at the reattachment point. Tests were made for the range of non-dimensional pitch rate from 0 to 0.25 and Reynolds number from 64,000 to 125,000. The results obtained suggest that the delay of the initiation of the leading edge vortex shedding is, at most, the same order of magnitude as the delay of the movement of the reattachment point. (Author).
Author: George Alvin Pierce
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages :
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Author: Myung J. Rhee
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 112
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Book Description
The purpose of this study is to examine the previously unpublished instantaneous pressure data of the Aeroflightdynamics Directorate Two-Dimensional (2D) and Three-Dimensional (3D) Oscillating Wing Experiment to better understand the process of dynamic stall vortex development on the NACA 0015 airfoil. This report presents representative 2D instantaneous pressure data for the upper and lower surfaces of the airfoil at various chordwise locations obtained at specific angles of attack during upstroke and downstroke cycles. Furthermore, the report contains a complete set of plots of instantaneous pressure distributions for the upper surface for all the 2D data sets obtained in the experiment. First, the lift, drag and pitching moment data of various testing conditions are reviewed and analyzed to classify the data both with and without a boundary layer trip into "no stall," "moderate stall," and "deep stall" data. Next, instantaneous pressure distributions on the upper surface of the airfoil are examined for the study of vortex development. The lift and pitching moment data are analyzed to document the dynamic overshoot which delays the development of the stall on the airfoil. Next, the range of angles of attack are selected where the lift and pitching moment data shows significant changes from unsteady flow behavior daring oscillation cycles. Furthermore, based on the unsteady flow characteristics found in each classification of dynamic stall, analysis is continued to identify the conditions where the reduced frequency clearly affects the unsteady flow behavior of the airfoil during the oscillation. This can result in a change of the dynamic stall classification of the airfoil response under various unsteady flow conditions. These conditions are discussed in detail in the comparative studies.
