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Velocity Profile Skin Friction Balance And Heat Transfer Measurements Of The Turbulent Boundary Layers At Mach 5 And Zero Pressure Gradient
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Book Synopsis Velocity Profile, Skin-friction Balance and Heat-transfer Measurements of the Turbulent Boundary Layers at Mach 5 and Zero-pressure Gradient by : Roland E. Lee
Download or read book Velocity Profile, Skin-friction Balance and Heat-transfer Measurements of the Turbulent Boundary Layers at Mach 5 and Zero-pressure Gradient written by Roland E. Lee and published by . This book was released on 1969 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a detailed experimental investigation of a two- dimensional turbulent boundary layer at zero-pressure gradient are presented. The studies were made at the free-stream Mach number of 5, momentum-thickness Reynolds number from 4800 to 56,000 and wall-to-adiabatic-wall temperature ratios from 0.5 to 1.0. The data are in analytical terms of velocity profile, temperature profile, law-of-the-wall, velocity-defect law and incompressible form factor. Comparisons of local skin-friction coefficients obtained by four different experimental methods are shown. An empirical equation was derived from the shear-balance data to calculate the friction coefficient from known values of Mach number, heat transfer and Reynolds number.
Book Synopsis VELOCITY PROFILE, SKIN-FRICTION BALANCE AND HEAT-TRANSFER MEASUREMENTS OF THE TURBULENT BOUNDARY LAYER AT MACH 5 AND ZERO-PRESSURE GRADIENT. by :
Download or read book VELOCITY PROFILE, SKIN-FRICTION BALANCE AND HEAT-TRANSFER MEASUREMENTS OF THE TURBULENT BOUNDARY LAYER AT MACH 5 AND ZERO-PRESSURE GRADIENT. written by and published by . This book was released on 1969 with total page 89 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a detailed experimental investigation of a two- dimensional turbulent boundary layer at zero-pressure gradient are presented. The studies were made at the free-stream Mach number of 5, momentum-thickness Reynolds number from 4800 to 56,000 and wall-to-adiabatic-wall temperature ratios from 0.5 to 1.0. The data are in analytical terms of velocity profile, temperature profile, law-of-the-wall, velocity-defect law and incompressible form factor. Comparisons of local skin-friction coefficients obtained by four different experimental methods are shown. An empirical equation was derived from the shear-balance data to calculate the friction coefficient from known values of Mach number, heat transfer and Reynolds number.
Book Synopsis Measurements of a Mach 4.9 Zero-pressure-gradient Turbulent Boundary Layer with Heat Yransfer by : Robert L. P. Voisinet
Download or read book Measurements of a Mach 4.9 Zero-pressure-gradient Turbulent Boundary Layer with Heat Yransfer written by Robert L. P. Voisinet and published by . This book was released on 1972 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Summary of Available Information on Reynolds Analogy for Zero-pressure-gradient, Compressible, Turbulent-boundary-layer Flow by : Aubrey M. Cary
Download or read book Summary of Available Information on Reynolds Analogy for Zero-pressure-gradient, Compressible, Turbulent-boundary-layer Flow written by Aubrey M. Cary and published by . This book was released on 1970 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Mathematical analysis of Reynolds analogy for turbulent heat transfer, skin friction, and boundary layer flow in adiabatic conditions.
Book Synopsis Direct Measurements of Turbulent Skin Friction on a Nonadiabatic Flat Plate at Mach Number 6.5 and Comparisons with Eight Theories by : Edward J. Hopkins
Download or read book Direct Measurements of Turbulent Skin Friction on a Nonadiabatic Flat Plate at Mach Number 6.5 and Comparisons with Eight Theories written by Edward J. Hopkins and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flow Visualization Studies of a Fin Protuberance Partially Immersed in a Turbulent Boundary Layer at Mach 5 by : Allen Edward Winkelmann
Download or read book Flow Visualization Studies of a Fin Protuberance Partially Immersed in a Turbulent Boundary Layer at Mach 5 written by Allen Edward Winkelmann and published by . This book was released on 1970 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: Various flow-visualization results are presented for a cylindrically blunted, unswept fin (yawed and unyawed) partially immersed in a turbulent boundary layer (delta approx. = 2.6 inches). The model, consisting of a fin-flat plate combination, was tested at a nominal Mach number of 5 and nominal free-stream Reynolds numbers per foot of 2800 000 and 7400 000. Azobenzene tests show regions of high heat transfer on the flat plate immediately upstream and downstream of the fin. Oil smear tests show in detail the surface shear directions and locations of separated flow which occur on the model. Schlieren and shadowgraph photographs indicate the complex shock wave structure which exists in front of the fin. A possible flow-field model is suggested to account for the observed flow patterns. (Author).
Download or read book NASA Technical Note written by and published by . This book was released on 1972 with total page 434 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Review of Turbulence Measurements in Compressible Flow by : Virgil A. Sandborn
Download or read book A Review of Turbulence Measurements in Compressible Flow written by Virgil A. Sandborn and published by . This book was released on 1974 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Compressible Turbulent Boundary Layers by :
Download or read book Compressible Turbulent Boundary Layers written by and published by . This book was released on 1969 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comparison of Prediction Methods and Studies of Relaxation in Hypersonic Turbulent Nozzle-wall Boundary Layers by : Dennis M. Bushnell
Download or read book Comparison of Prediction Methods and Studies of Relaxation in Hypersonic Turbulent Nozzle-wall Boundary Layers written by Dennis M. Bushnell and published by . This book was released on 1969 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbulent boundary layer measurements on axisymmetric hypersonic nozzle walls.
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient by : David L. Brott
Download or read book An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient written by David L. Brott and published by . This book was released on 1969 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: The paper describes the results of a detailed experimental investigation of a two-dimensional turbulent boundary layer in a favorable pressure gradient where the free-stream Mach number varied from 3.8 to 4.6 and the ratio of wall to adiabatic-wall temperature has a nominal value of 0.82. Detailed profile measurements were made with pressure and temperature probes; skin friction was measured directly with a shear balance. The velocity- and temperature-profile results were compared with zero pressure gradient and incompressible results. The skin-friction data were correlated with momentum-thickness Reynolds number and pressure-gradient parameter. (Author).
Book Synopsis A Forward Facing Step Study by : Richard T. Driftmyer
Download or read book A Forward Facing Step Study written by Richard T. Driftmyer and published by . This book was released on 1973 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation involving a thick, adiabatic, naturally turbulent, two-dimensional boundary layer undergoing separation has been completed at the Naval Ordnance Laboratory (NOL). Forward facing steps (with attached end plates) were used to induce boundary-layer separation for the particular case where the step heights, h, were less than the boundary-layer thickness, delta. The tests were conducted at a free-stream Mach number of 4.9 with a range of unit Reynolds numbers varying from 0.8 x 10 to the 6th power per foot to 4.0 x 10 to the 6th power per foot. The pressure distributions measured in the separated region ahead of the steps were found to be functions of both Re sub delta and h/delta for the turbulent boundary-layer separation case where h
Book Synopsis An Experimental Investigation of the Surface Pitot Probe Including Effects of Heat Transfer and Compressibility by : David L. Brott
Download or read book An Experimental Investigation of the Surface Pitot Probe Including Effects of Heat Transfer and Compressibility written by David L. Brott and published by . This book was released on 1968 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the experimental investigation of surface Pitot probe in both subsonic and supersonic flow. The effect of heat transfer on the results was also investigated in supersonic flow. (Author).
Download or read book AIAA 74-51 - AIAA 74-100 written by and published by . This book was released on 1974 with total page 656 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research Abstracts and Reclassification Notice by : United States. National Advisory Committee for Aeronautics
Download or read book Research Abstracts and Reclassification Notice written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 716 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1973 with total page 528 pages. Available in PDF, EPUB and Kindle. Book excerpt:
