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Measurements Of A Mach 49 Zero Pressure Gradient Turbulent Boundary Layer With Heat Yransfer
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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 Measurements of a Mach 4.9 Zero-Pressure-Gradient Turbulent Boundary Layer with Heat Transfer. Part 1. Data Compilation by : Robert L. P. Voisinet
Download or read book Measurements of a Mach 4.9 Zero-Pressure-Gradient Turbulent Boundary Layer with Heat Transfer. Part 1. Data Compilation written by Robert L. P. Voisinet and published by . This book was released on 1972 with total page 105 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 The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers by : Roger L. Kimmel
Download or read book The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers written by Roger L. Kimmel and published by . This book was released on 1993 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
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 Comparisons of Turbulent-boundary-layer Measurements at Mach Number 19.5 with Theory and an Assessment of Probe Errors by : Ivan E. Beckwith
Download or read book Comparisons of Turbulent-boundary-layer Measurements at Mach Number 19.5 with Theory and an Assessment of Probe Errors written by Ivan E. Beckwith and published by . This book was released on 1971 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of total temperature and pitot pressure across boundary layer of test section wall of axisymmetric contoured nozzle at hypersonic speed in nitrogen.
Book Synopsis Calculation of Turbulent Boundary Layers with Heat Transfer and Pressure Gradient Utilizing a Compressibility Transformation. Part 1: Summary Report by : C. Economos
Download or read book Calculation of Turbulent Boundary Layers with Heat Transfer and Pressure Gradient Utilizing a Compressibility Transformation. Part 1: Summary Report written by C. Economos and published by . This book was released on 1971 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6 by : Mitchel H. Bertram
Download or read book Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6 written by Mitchel H. Bertram and published by . This book was released on 1959 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of the High Speed Turbulent Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient. Part 1 - Summary Report by :
Download or read book An Investigation of the High Speed Turbulent Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient. Part 1 - Summary Report written by and published by . This book was released on 1970 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Turbulent Boundary Layer at a Mach Number of 6 with Heat Transfer at High Reynolds Numbers by : Richard D. Samuels
Download or read book Experimental Investigation of the Turbulent Boundary Layer at a Mach Number of 6 with Heat Transfer at High Reynolds Numbers written by Richard D. Samuels and published by . This book was released on 1967 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analytical, Numerical, and Experimental Results on Turbulent Boundary Layers by : David L. Whitfield
Download or read book Analytical, Numerical, and Experimental Results on Turbulent Boundary Layers written by David L. Whitfield and published by . This book was released on 1976 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the results of analytical, numerical, and experimental investigations of incompressible and compressible boundary layers. The subjects considered are (1) Laminar and/or turbulent numerical boundary-layer calculations in which the Reynolds stress is related to the turbulent kinetic energy; (2) an analytical investigation of turbulence near a wall which is not founded on classical mixing-length theory; (3) analytical solutions for relating velocity and temperature throughout turbulent boundary layers for nonunity Prandtl numbers; (4) a description of the data reduction of pitot pressure measurements utilizing these analytical results, and (5) the application of the numerical and analytical results to the analysis of turbulent boundary-layer measurements made in the Propulsion Wind Tunnel Facility (PWT).
Download or read book NASA Technical Note written by and published by . This book was released on 1973 with total page 784 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of the High Speed Turbulent Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient: The Compressibility transformation by : Constantino Economos
Download or read book An Investigation of the High Speed Turbulent Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient: The Compressibility transformation written by Constantino Economos and published by . This book was released on 1970 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report investigates the behavior of high speed turbulent boundary layer with heat transfer and streamwise pressure gradient.
Book Synopsis A Re-Evaluation of Zero Pressure Gradient Compressible Turbulent Boundary Layer Measurements by : James E. Danberg
Download or read book A Re-Evaluation of Zero Pressure Gradient Compressible Turbulent Boundary Layer Measurements written by James E. Danberg and published by . This book was released on 1973 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A number of compressible turbulent boundary layer velocity and temperature profiles with zero pressure gradient were collected and prepared for computer analysis. An assumed equation for these profiles was chosen allowing four constants to be adjusted by a nonlinear least squares technique to fit the experimental data. The four constants are: velocity scale, boundary layer thickness, constant of the semi-log region, and wake constant. This equation is analogous to Cole's incompressible law of the wall and wake but uses a generalized velocity to account for compressibility. Measurements from 45 adiabatic wall tests were analyzed covering a Mach number range from 2 to 6 and a momentum thickness Reynolds number range from 2300 to 750,000. (Modified author abstract).
Book Synopsis Calculation of Compressible Turbulent Boundary Layers with Pressure Gradients and Heat Transfer by : Larry L. Lynes
Download or read book Calculation of Compressible Turbulent Boundary Layers with Pressure Gradients and Heat Transfer written by Larry L. Lynes and published by . This book was released on 1969 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of the High Speed Turbulent Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient. Part 2 - The Compressibility Transformation - General Considerations by :
Download or read book An Investigation of the High Speed Turbulent Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient. Part 2 - The Compressibility Transformation - General Considerations written by and published by . This book was released on 1970 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis High Mach Number Turbulent Boundary Layer with and Without Favorable Pressure Gradient by : NEW YORK UNIV WESTBURY AEROSPACE AND ENERGETICS LAB.
Download or read book High Mach Number Turbulent Boundary Layer with and Without Favorable Pressure Gradient written by NEW YORK UNIV WESTBURY AEROSPACE AND ENERGETICS LAB. and published by . This book was released on 1975 with total page 133 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary layer profiles of total temperature and total pressure, together with surface pressure and heat transfer rates, in turbulent boundary layers with and without favorable pressure gradients have been measured with a Mach 6 wind tunnel facility. Experimental results were correlated and comparisons between the cases with and without favorable pressure gradient were made. Effects of pressure gradient and upstream history to the boundary layer development were investigated. Numerical results of an existing turbulent boundary layer theory were also compared with present experiments.
Book Synopsis Experimental Investigation of a Turbulent Boundary Layer at Mach 6, High Reynolds Numbers, and Zero Heat Transfer by : Jerry B. Adcock
Download or read book Experimental Investigation of a Turbulent Boundary Layer at Mach 6, High Reynolds Numbers, and Zero Heat Transfer written by Jerry B. Adcock and published by . This book was released on 1965 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
