Contributions to the Experimental Investigation and Analysis of Aerofoil Dynamic Stall PDF Download
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Author: John Gordon Leishman
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Languages : en
Pages :
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Author: John Gordon Leishman
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Category :
Languages : en
Pages :
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Author: Katie Kristine Thorne
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Category :
Languages : en
Pages : 101
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Author: Andrew James Niven
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Category : Aerofoils
Languages : en
Pages :
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Author:
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ISBN:
Category :
Languages : en
Pages : 662
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Author: Lup Yun Seto
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Category : Aerodynamics
Languages : en
Pages :
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Author: G. M. Graham
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Category : Aerofoils
Languages : en
Pages : 102
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Author: Michael S. Francis
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Category : Aerofoils
Languages : en
Pages :
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"The results of an experimental investigation of airfoil dynamic stall involving large amplitude pitching motions are described. The discussion is focused on constant pitch rate motion histories. Measurements of unsteady surface pressure distributions for both NACA 0012 and NACA 64 sub 1 A012(13) profiles have been employed to infer the onset and evolution of an energetic leading edge separation vortex over a wide range of flow and motion conditions. These data have also been integrated to provide estimates of the time histories of the lift, pressure drag and moment coefficients. The effectiveness of the various motions for achieving lift enhancement has been determined through the introduction of a dimensionless impulse parameter which accounts for both the magnitude and duration of the additional lift increment during the post-stall period."--Abstract, report documention p.
Author: Michel Pascazio
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Category :
Languages : en
Pages :
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Author: K. W. McAlister
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Category :
Languages : en
Pages : 639
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Author: Koji Isogai
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Category : Aerofoils
Languages : en
Pages : 19
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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).
