Author: Aubrey M. CaryPublisher:
ISBN:
Category : Reynolds analogy
Languages : en
Pages : 28
Book Description
Mathematical analysis of Reynolds analogy for turbulent heat transfer, skin friction, and boundary layer flow in adiabatic conditions.
Summary of Available Information on Reynolds Analogy for Zero-pressure-gradient, Compressible, Turbulent-boundary-layer Flow
Author: Aubrey M. CaryPublisher:
ISBN:
Category : Reynolds analogy
Languages : en
Pages : 28
Book Description
Mathematical analysis of Reynolds analogy for turbulent heat transfer, skin friction, and boundary layer flow in adiabatic conditions.
Summary of Available Information on Reynolds Analogy for Zero-pressure-gradient, Compressible, Turbulent-boundary-layer Flow
Author: Aubrey M. CaryAn Approximate Method for the Calculation of the Reynolds Analogy Factor for a Compressible Turbulent Boundary Layer in a Pressure Gradient
Author: Neal TetervinPublisher:
ISBN:
Category : Enthalpy
Languages : en
Pages : 96
Book Description
The method predicts that a positive pressure gradient increases and a negative pressure gradient decreases the ratio of Stanton number to friction coefficient. The Crocco relation between the velocity and total enthalpy for a non-adiabatic surface and zero pressure gradient is generalized to non-zero pressure gradient. The relation between the velocity and the total enthalpy varies markedly from the flat plate Crocco relation as the pressure gradient departs from zero. The magnitude of the variation depends on the velocity profile shape parameter. (Author).
NASA Technical Note
Author: NASA Technical Paper
Author: Turbulent-boundary-layer Heat-transfer and Transition Measurements with Surface Cooling at Mach 6
Author: Aubrey M. CaryScientific and Technical Aerospace Reports
Author: Measurements of a Mach 4.9 Zero-pressure-gradient Turbulent Boundary Layer with Heat Yransfer
Author: Robert L. P. VoisinetPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 128
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).
Monthly Catalog of United States Government Publications, Cumulative Index
Author: United States. Superintendent of DocumentsPublisher:
ISBN:
Category : United States
Languages : en
Pages : 1504
Book Description
Aeronautical Engineering
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 648
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).