Boundary Layer Measurements in an Accelerated Flow with and Without Heat Transfer PDF Download
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Author: Howard L. Wesoky
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 52
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Book Description
Author: Howard L. Wesoky
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 52
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Book Description
Author: Howard L. Wesoky
Publisher:
ISBN:
Category : Axial flow
Languages : en
Pages : 40
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Book Description
Author: Paul F. Brinich
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 36
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Book Description
An analysis of time-mean-turbulent boundary layer velocity profiles measured in a rapidly accelerating flow suggests that the outer region of the velocity profiles consists of essentially inviscid, rotational flow. The extent of this inviscid outer region was observed in some cases to exceed 90 percent of what is ordinarily thought of as the turbulent boundary layer thickness. On the other hand, the inner frictional region of these velocity profiles appears to have turbulent characteristics similar to those of more conventional turbulent boundary layers. Hence, the outer edge boundary condition for this inner region is more properly the external rotational flow region than the free stream.
Author: Donald R. Boldman
Publisher:
ISBN:
Category : Anemometer
Languages : en
Pages : 44
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Book Description
Hot-wire anemometer for velocity, intermittancy, and turbulence intensity measurements in boundary layer of accelerated flow.
Author: Ralph John Volino
Publisher:
ISBN:
Category :
Languages : en
Pages : 492
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 544
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Author: Donald R. Boldman
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 42
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Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 188
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Author: Donald R. Boldman
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 68
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Book Description
A review of a comprehensive experimental investigation of the heat transfer and boundary layer in 30 deg to 15 deg and 60 deg to 15 deg conical nozzles is presented. The experiments were conducted with air at a stagnation temperature of 539 K (970 R) and throat Reynolds numbers based on a diameter ranging from 6 x 10 to the 5th power to 5 x 10 to the 6th power. Nozzle wall surface finish was varied from a smooth machine finish to a 826 x 10 to the minus 6th power cm (325 x 10 to the minus 6th in.) rms sandblasted finish. Measured heat transfer and wall temperatures are tabulated.
Author: Jet Propulsion Laboratory (U.S.)
Publisher:
ISBN:
Category : Space flight
Languages : en
Pages : 390
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Book Description
