Heat Transfer to Boundary Layers with Pressure Gradients PDF Download
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Author: Ralph Alois Seban
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 194
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Book Description
Author: Ralph Alois Seban
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 194
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Book Description
Author: Roger L. Kimmel
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 46
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Book Description
Boundary layer transition was measured in zero, favorable, and adverse pressure gradients at Mach 8 using heat transfer. Models consisted of 7 degrees half angle forecones 0.4826 m long, followed by flared or ogive aft bodies 0.5334 m long. The flares and ogives produced constant pressure gradients. For the cases examined, favorable pressure gradients delay transition and adverse pressure gradients promote transition, but transition zone lengths are shorter in favorable pressure gradient. Results of the effect of adverse pressure gradient on transition zone lengths were inconclusive.
Author: Yaning Lu
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 158
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Book Description
Author: Shimer Zane Pinckney
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 68
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Book Description
Author: Ralph Alois Seban
Publisher:
ISBN:
Category : Aerothermodynamics
Languages : en
Pages : 88
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Book Description
Author: John Boyd Bell
Publisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 256
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Book Description
Author: Larry L. Lynes
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 148
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Book Description
Author: Suhas V. Patankar
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 248
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Book Description
Author: Robert L. P. Voisinet
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 128
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Book Description
The results of a detailed experimental investigation of the compressible turbulent boundary layer in a zero-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall for a nominal Mach number of 4.9, at momentum thickness Reynolds numbers from 7,000. to 58,000. and at wall-to-adiabatic-wall temperature ratios of 1.0, 0.8 and 0.25. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. Furthermore, the wall shear and surface heat transfer were measured directly with a skin-friction balance and a heat-transfer gage, respectively. (Author Modified Abstract).
Author: J. S. Hahn
Publisher:
ISBN:
Category :
Languages : en
Pages : 57
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Book Description
An experimental investigation of the behavior of a turbulent boundary layer subjected to adverse and favorable pressure gradients was conducted at Mach number 4 for a free-stream Reynolds number of 0.500,000 per inch. Two severe pressure gradients were imposed on the boundary layer by interchangeable contoured centerbodies inside a large hollow cylinder for cold-wall and adiabatic-wall temperature conditions. Imposition of either of the adverse pressure gradients significantly decreased the natural growth rate of the boundary-layer displacement thickness, whereas the favorable pressure gradient had opposite effects; momentum thickness was relatively unaffected by pressure gradient. A pressure gradient increase of about 30 percent caused relatively small changes in the skin friction, heat-transfer rate, and the characteristic boundary-layer parameters. Wall cooling effects (T sub w/t sub 0 approximately 0.3) on the boundary-layer thickness parameters were nearly insignificant, in comparison with the adiabatic-wall results. Heat-transfer distributions were similar to the local skin friction results based on free-stream conditions. (Author).
