The Effect of Centrifugal Forces on Boundary Layer Transition for a Highly Heated Body PDF Download
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Author: Eugene Sevigny
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 50
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Author: Eugene Sevigny
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 50
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Author: Eugene Sevigny
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ISBN:
Category :
Languages : en
Pages : 0
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Author: Ernst Rudolf Georg Eckert
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 118
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Author: United States. Wright Air Development Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1276
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Author: Lester Lees
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ISBN:
Category :
Languages : en
Pages : 6
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At high supersonic flight speeds or with a highly cooled surface, there is a strong density gradient across the boundary layer. Close to the surface the gas is cool and of low-temperature molecular weight; at the outer edge of the boundary layer the gas is hot and may be partially dissociated, so that its density is lower by a factor of 10 - 20. At the same time a strong centrifugal acceleration is produced by the body curvature, and this outward acceleration acts in the direction of decreasing density. The question arises as to whether this destabilizing effect of the acceleration field in a density gradient is sufficient to overcome the stabilizing effect of the increasing angular momentum of the fluid in the outward direction. The conclusion is drawn that the strong stabilizing effect of the outward increase in angular momentum is always dominant in the laminar boundary layer. (Author).
Author: Morton Cooper
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 42
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Author:
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ISBN:
Category : Science
Languages : en
Pages : 262
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Author: K. R. Czarnecki
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Category : Body of revolution
Languages : en
Pages : 23
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A preliminary investigation has been made of the effects of heat transfer on boundary-layer transition on a body of revolution at a Mach number of 1.61 and over a Reynolds number range of 7,000,000 to 20,000,000, based on body length. The body had a parabolic-arc profile, blunt-base, and a fineness ratio of 12.2 (NACA RM-10). The results indicated that, by cooling the model an average of about 50 degrees F, the Reynolds number for which laminar boundary-layer flow could be maintained over the entire length of the body was increased from the value of 11,500,000 without cooling to over 20,000,000, the limit of the present tests. Heatig the model an average of about 12 degrees F on the other hand decreased the transition Reynolds number from 11,500,000 to about 8,000,000. These effects of heat transfer on transition were considerably larger than previously found in similar investigations in other wind tunnels. It appears that, if the boundary-layer transition Reynolds number for zero heat transfer is large, as in the present experiments, then the sensitivity of transition to heating or cooling is high; if the zero-heat-transfer transition Reynolds number is low, then transition is relatively insensitive to heat-transfer effects.
Author: George E. Kaattari
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 74
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Author:
Publisher:
ISBN:
Category : Weights and measures
Languages : en
Pages : 786
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