Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers PDF Download
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Author: David F. Gates
Publisher:
ISBN:
Category : Supersonic nozzles
Languages : en
Pages : 124
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Book Description
The report describes an experimental study of compressible turbulent boundary layers for which the upstream history was systematically varied. A series of experiments was conducted using both a supersonic half nozzle and a conventional flat plate for which the nozzle throat and flat plate leading edge can be temperature controlled. The supersonic nozzle provided a favorable upstream pressure gradient together with a controlled thermal history at the throat. The flat plate provided upstream temperature control with no pressure history. Velocity and temperature profile and heat-transfer measurements were made in a downstream region of zero-pressure-gradient and constant wall temperature. (Modified author abstract).
Author: David F. Gates
Publisher:
ISBN:
Category : Supersonic nozzles
Languages : en
Pages : 124
Get Book Here
Book Description
The report describes an experimental study of compressible turbulent boundary layers for which the upstream history was systematically varied. A series of experiments was conducted using both a supersonic half nozzle and a conventional flat plate for which the nozzle throat and flat plate leading edge can be temperature controlled. The supersonic nozzle provided a favorable upstream pressure gradient together with a controlled thermal history at the throat. The flat plate provided upstream temperature control with no pressure history. Velocity and temperature profile and heat-transfer measurements were made in a downstream region of zero-pressure-gradient and constant wall temperature. (Modified author abstract).
Author: David F. Gates
Publisher:
ISBN:
Category :
Languages : en
Pages : 101
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Book Description
The report describes an experimental study of compressible turbulent boundary layers for which the upstream history was systematically varied. A series of experiments was conducted using both a supersonic half nozzle and a conventional flat plate for which the nozzle throat and flat plate leading edge can be temperature controlled. The supersonic nozzle provided a favorable upstream pressure gradient together with a controlled thermal history at the throat. The flat plate provided upstream temperature control with no pressure history. Velocity and temperature profile and heat-transfer measurements were made in a downstream region of zero-pressure-gradient and constant wall temperature. (Modified author abstract).
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 814
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Book Description
Author:
Publisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 580
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Book Description
Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 826
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 768
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Book Description
Author:
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 1000
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 344
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Book Description
Author: Edwin J. Saltzman
Publisher:
ISBN:
Category : Skin friction (Aerodynamics)
Languages : en
Pages : 52
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Book Description
Author: Robert L. P. Voisinet
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 144
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Book Description
The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).
