Leading Edge Effect on Separated Supersonic Flows. Contract Nr AF 61 052-350 PDF Download
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Category :
Languages : en
Pages : 0
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Category :
Languages : en
Pages : 0
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Author: Jean J. Ginoux
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Category : Aerodynamics, Supersonic
Languages : en
Pages : 774
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Author: Defense Documentation Center (U.S.)
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Category : Military art and science
Languages : en
Pages : 1540
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Author: Jean J. Ginoux
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Category : Aerodynamics, Supersonic
Languages : en
Pages : 1
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In supersonic tunnel tests with a two-dimensional backward-facing step model, span-wise perturbations were found in the reattachment region. Studies were made using the same and other similar models. In these later studies, the same three-dimensional perturbations were detected, into the full thickness of the boundary-layer, after reattachment, both in turbulent and laminar regions of the flow. Their amplitude was a maximum in the transition region. Using a model with a much improved accuracy of manufacture, notably at the leading-edge, it was found that the amplitude of the perturbations was greatly reduced, roughly in proportion to the size of the irregularities of manufacture of the leadingedge itself. It is concluded that the phenomenon is essentially one of instability in the twodimensional flow, the main triggering action arising from small irregularities in the leading edge.
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Category :
Languages : en
Pages : 2180
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Category : Union catalogs
Languages : en
Pages : 632
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Includes entries for maps and atlases.
Author: Jean J. Ginoux
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 1
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An experimental investigation was made on laminar separated supersonic streams using two-dimensional backward-facing step models. It was shown that a cross-flow existed in the separated region of the flow which is associated with the side wall boundary-layers. Its effect is to decrease the base pressure and increase the pressure gradient at reattachment even for large values of the model-span to step-height ratio. It is shown that the commonly accepted assumption that a twodimensional flow exists when there is no measurable spanwise pressure variation is a necessary but not sufficient condition. In the turbulent case, it is generally found that the measured base pressure is lower than is theoretically predicted. This is explained by the existence of a cross-flow (suction) produced by strong vertical vortices near the side walls. (Author).
Author:
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Category : Aeronautics
Languages : en
Pages : 788
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Author: United States. Air Force. Office of Aerospace Research
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Category : Aeronautics, Military
Languages : en
Pages : 800
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Author:
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Category : Science
Languages : en
Pages : 1722
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