Author: Robert J. Vidal
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 118

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Author: Robert J. Vidal
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 82

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The effects of stre m v locity gradient on airfoil maximum lift are defined with experiment l da a ob ained in a simulated two-dimensional slipstream. The experime t l results show that w en po itioned near the slips ream plane of symmetry, the airfoil m ximum lift vari s markedly with location in the slipstream. In movi g he irfoil from abov to below the slipstream plane of symmetry through a total distance corresponding to the airfoil thickne s, force data and boundary-lay r observations show that boundary-layer separation is delayed to higher angle of a ck, a d the airfoil maximum lift is doubled. It is concluded that the destalling effect ob erved in t nonu ifor lipstream is o associated wit slipstream bou ry interferenc but stems from the influence of e large local slipstream shear on airfoil characteristics The effects of uniform no uniform shear on airfoil lift and pres ure dis ribution are discussed, within the framework of existing first-order, small-shear theory, to show that t ese effects of shear tend to promote stall. A Pohlhausen calculation of th laminary boundary layer in a stream with s ar is used to identify an to as ess the eff cts of stream shear on boundary-layer separation criteria.

Author: Gary R. Ludwig
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36

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A theoretical and experimental program was conducted to investigate the aerodynamics of an airfoil in a two-dimensional nonuniformly sheared slipstream. A mathematical model was developed to predict airfoil pressure distributions in such a slipstream and was used successfully for slipstreams with moderate shear. Pressure distributions over a wide angle of attack range were measured experimentally on an airfoil at each of seven different locations in a highly sheared two-dimensional slipstream. Study of the pressure distributions obtained on the airfoil at a location slightly above the flow centerline and also at a location slightly below the flow centerline indicates that the large effects on stalling characteristics are due to differences in the upper surface pressure distributions. These pressure distributions are affected by the freestream shear. Moreover, in the data obtained for airfoils located near the flow centerline, the differences in the lift appear to be caused primarily by differences in the stagnation pressure of the streamline which intersects the airfoil. This stagnation pressure is a function not only of airfoil location relative to the slipstream, but also of the angle of attack of the airfoil. (Author).

Author: Robert J. Vidal
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 62

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Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 818

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Author:
Publisher:
ISBN:
Category : Military research
Languages : en
Pages :

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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580

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Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)

Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 464

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Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 568

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Author:
Publisher:
ISBN:
Category : Military research
Languages : en
Pages : 746

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