Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Turbulent Boundary Layer Measurements At Hypersonic Mach Numbers
Download Turbulent Boundary Layer Measurements At Hypersonic Mach Numbers full books in PDF, epub, and Kindle. Read online Turbulent Boundary Layer Measurements At Hypersonic Mach Numbers ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Turbulent Boundary Layer Measurements at Hypersonic Mach Numbers by : Anthony W. Fiore
Download or read book Turbulent Boundary Layer Measurements at Hypersonic Mach Numbers written by Anthony W. Fiore and published by . This book was released on 1970 with total page 87 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the structure and integrated properties of turbulent boundary layers at hypersonic speeds. These properties were deduced from pitot pressure and total temperature surveys made through the boundary layer at various locations on the wall of both a contoured and a conical nozzle. Tests were conducted at average Mach numbers of 11.89 and 10.83 respectively. The corresponding momentum Reynolds numbers ranged from 650 to approximately 1330. The data were obtained in the presence of both a favorable pressure gradient and heat transfer. The results indicate that the density distribution, the static temperature distribution, and the total enthalpy ratio versus the velocity ratio profiles through the boundary layer do not agree with the Crocco theory. The data also indicate that the sublayer is very thick and is approximately 25% as thick as the boundary layer itself. Depending upon the momentum Reynolds number, the sublayer can be either fully subsonic or partially subsonic and partially supersonic in nature. In addition, the transformed velocity profile data and the law of the wall in its incompressible form do not agree. Finally, the skin friction coefficient obtained from the Baronti-Libby transformation and Coles' law of corresponding stations is about 15% to 35% greater than that calculated using the Spalding-Chi semi-empirical technique. (Author).
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 A Method of Calculating Turbulent-boundary-layer Growth at Hypersonic Mach Numbers by : James C. Sivells
Download or read book A Method of Calculating Turbulent-boundary-layer Growth at Hypersonic Mach Numbers written by James C. Sivells and published by . This book was released on 1959 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is developed for calculating the growth of a turbulent boundary layer at hypersonic Mach numbers. Excellent agreement with experimental results from axisymmetric nozzles has been obtained by the application of this method. The method utilizes a modification of Stewartson's transformation to simplify the integration of the momentum equation. Heat transfer is taken into account by evaluating the gas properties at Eckert's reference temperature and by using a modification of Crocco's quadratic for the temperature distribution in the boundary layer. A new empirical relation is used for the incompressible friction coefficient which agrees with experimental data over a Reynold's number range from 10(superscript 5) to 10(superscript 9).
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 Fluctuating Properties of Turbulent Boundary Layers for Mach Numbers Up to 9 by : William D. Harvey
Download or read book Fluctuating Properties of Turbulent Boundary Layers for Mach Numbers Up to 9 written by William D. Harvey and published by . This book was released on 1969 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Fluctuating properties of turbulent boundary layers for Mach numbers up to 9.
Book Synopsis Experimental Study of Nozzle Wall Boundary Layers at Mach Numbers 20 to 47 by : Joseph H. Kemp
Download or read book Experimental Study of Nozzle Wall Boundary Layers at Mach Numbers 20 to 47 written by Joseph H. Kemp and published by . This book was released on 1972 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: The nozzle wall boundary layer of an M-50 helium tunnel was investigated with pitot pressure, total temperature, skin friction, and wall heat transfer measurements at five stations and hot wire measurements at two stations. The results indicated that the boundary layer was turbulent with a thick viscous sublayer. Pressure gradients were observed across the boundary layer; the effect of these gradients on the equations of motion are discussed. The direct skin friction measurements were higher than expected from empirical predictions; the Reynolds analogy factors however were lower than expected. Hot wire measurements indicated mass flow fluctuations as large as 80 percent of the local mean mass flow at the edge of the viscous sublayer with a maximum value relative to the edge mass flow of about 15 percent at gamma about equal to 0.8.
Book Synopsis Measurements of Hypersonic Turbulent Heat Transfer on a Highly Cooled Cone by : Donald M. Wilson
Download or read book Measurements of Hypersonic Turbulent Heat Transfer on a Highly Cooled Cone written by Donald M. Wilson and published by . This book was released on 1967 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbulent boundary layer heat transfer rates were measured on a thin-walled slender cone at a free-stream Mach number of 5.0. Wall to stagnation temperature ratios from 0.15 to 0.40 were obtained by pre-cooling the model using liquid nitrogen. Tests at a wide range of Reynolds numbers were conducted by varying the tunnel supply pressure; thus providing data for both laminar and mixed laminar-turbulent types of boundary layers. The experimental results obtained were compared with existing theories which predict convective heat transfer coefficients. These comparisons indicate that the data corresponding to a 760R supply temperature verify the predictions of Winkler and Cha; however, data acquired at a supply temperature of 1160R substantiate the predictions of Spalding and Chi. (Author).
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 Documentation of Two- and Three-dimensional Hypersonic Shock Wave/turbulent Boundary Layer Interaction Flows by : Marvin I. Kussoy
Download or read book Documentation of Two- and Three-dimensional Hypersonic Shock Wave/turbulent Boundary Layer Interaction Flows written by Marvin I. Kussoy and published by . This book was released on 1989 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Assessment of a Transitional Boundary Layer Theory at Low Hypersonic Mach Numbers by : S. J. Shamroth
Download or read book Assessment of a Transitional Boundary Layer Theory at Low Hypersonic Mach Numbers written by S. J. Shamroth and published by . This book was released on 1972 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was carried out to assess the accuracy of a transitional boundary layer theory in the low hypersonic Mach number regime. The theory is based upon the simultaneous numerical solution of the boundary layer partial differential equations for the mean motion and an integral form of the turbulence kinetic energy equation which controls the magnitude and development of the Reynolds stress. Comparisions with experimental data show the theory is capable of accurately predicting heat transfer and velocity profiles through the transitional regime and correctly predicts the effects of Mach number and wall cooling on transition Reynolds number. The procedure shows promise of predicting the initiation of transition for given free stream disturbance levels. The effects on transition predictions of the pressure dilitation term and of direct absorption of acoustic energy by the boundary layer were evaluated.
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 Transition Fixing for Hypersonic Flow by :
Download or read book Transition Fixing for Hypersonic Flow written by and published by . This book was released on 1967 with total page 28 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 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 90 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 Mean Flow Measurements in a Hypersonic Turbulent Boundary Layer by : Arnold J. Laderman
Download or read book Mean Flow Measurements in a Hypersonic Turbulent Boundary Layer written by Arnold J. Laderman and published by . This book was released on 1971 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was carried out to determine the structure of the turbulent boundary layer on the wall of the Jet Propulsion Laboratory Hypersonic Wind Tunnel at a free-stream Mach number of 9.37. Profiles of flow properties were obtained from pitot pressure, static pressure, and total temperature surveys made through the 6 inch thick boundary layer at a station 160 inches from the nozzle throat. Tests were conducted primarily for the following conditions: unit free-stream Reynolds number of 127,000 per inch, corresponding to a Reynolds number based on momentum thickness of 36,800, and a wall to free-stream total temperature ratio of 0.385. A cursory examination of the boundary layer was also made at a unit stream Reynolds number of 67,000. The static pressure measurements, although indicating negligible streamwise variation, revealed the existence of a significant pressure gradient normal to the wall, with the pressure at the wall approximately 45% greater than its free-stream value.
Book Synopsis Turbulent Boundary Layer Displacement Effects in Hypersonic Flow by : R. M. Grabow
Download or read book Turbulent Boundary Layer Displacement Effects in Hypersonic Flow written by R. M. Grabow and published by . This book was released on 1967 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fluctuation Measurements in Supersonic Turbulent Boundary Layers by : Alan. L. Kistler
Download or read book Fluctuation Measurements in Supersonic Turbulent Boundary Layers written by Alan. L. Kistler and published by . This book was released on 1958 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
