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Turbulent Boundary Layer Characteristics In Supersonic Streams Having Adverse Pressure Gradients
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Book Synopsis Turbulent Boundary Layer Characteristics in Supersonic Streams Having Adverse Pressure Gradients by : George H. McLafferty
Download or read book Turbulent Boundary Layer Characteristics in Supersonic Streams Having Adverse Pressure Gradients written by George H. McLafferty and published by . This book was released on 1959 with total page 248 pages. Available in PDF, EPUB and Kindle. Book excerpt: Inestigations were conducted to determine the thickness and profile shape characteristics of turbulent boundary layers in supersonic streams having adverse pressure gradients similar to those which are encountered in supersonic inlets. The program included tests conducted at Mach numbers from 2.0 to 3.5 using two-dimensional and axisymmetric curved-surface models to produce the adverse pressure gradients. The magnitude of the gradients relative to the boundary layer thickness at the beginning of the gradient was varied by employing models having different radii of curvature and by changing the boundary layer thickness at the beginning of the gradient. The over-all pressure rise in most cases was greater than the value which would cause a turbulent boundary layer to separate if the pressure rise were created by an oblique shock wave. Some tests were conducted to determine the effect of boundary layer removal from the curved surfaces on boundary layer growth and on the pressure gradients which could be realized without separation. An analytical investigation was also conducted so that the results of the experimental investigation could be applied to the prediction of cases outside the range of the experiments. (Author).
Book Synopsis Supersonic Turbulent Boundary Layer Growth Over Cooled Walls in Adverse Pressure Gradients by : C. E. KEPLER
Download or read book Supersonic Turbulent Boundary Layer Growth Over Cooled Walls in Adverse Pressure Gradients written by C. E. KEPLER and published by . This book was released on 1962 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: The characteristics of supersonic turbulent boundary layers on cooled surfaces having adverse pressure gradients were investigated to provide design information for hypersonic inlets. Tests were conducted at Mach numbers of 3 and 6 with values of wall temperature as low as 30% of the adiabatic recovery temperature. The adverse pressure gradients were generated by two-dimensional model including a circular-arc surface, an isentropic-compression surface, and an oblique shock generator. Velocity and temperature profiles through the boundary layer were obtained and the integral boundary layer parameters were evaluated along the surface. An analytical investigation was also conducted to provide a basis for evaluating the experimental results. It was found that cooled, turbulent boundary layers in adverse pressure gradients are thinner and less distorted than uncooled boundary layers, that the ratio of Stanton number to skin-friction coefficient is higher than the flat-plate value, and t at the total amount of heat removed is greater than that predicted by integrating local heat-transfer rates based on flat-plate conditions al ng the surface. (Author).
Book Synopsis The Supersonic Turbulent Boundary Layer in an Adverse Pressure Gradient--Experiment and Data Analysis by : Walter B. Sturek
Download or read book The Supersonic Turbulent Boundary Layer in an Adverse Pressure Gradient--Experiment and Data Analysis written by Walter B. Sturek and published by . This book was released on 1973 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental measurements of the profile characteristics of the supersonic turbulent boundary layer in a region of moderate adverse pressure gradient and an analysis of the data are reported. The data are for a closely adiabatic wall at a tunnel nozzle setting of M = 3.54. All measurements necessary for a complete set of profile data were made. Turbulent boundary layer equations are analyzed by numerical integration using the tabulated profile data. The data correlated in law of the wall and velocity defect dimensionless coordinates using an integral compressibility transformation. Distributions of eddy viscosity and mixing length are calculated using the mean profile data. (Author).
Book Synopsis Approximate Turbulent Boundary-layer Development in Plane Compressible Flow Along Thermally Insulated Surfaces with Application to Supersonic-tunnel Contour Correction by : Maurice Tucker
Download or read book Approximate Turbulent Boundary-layer Development in Plane Compressible Flow Along Thermally Insulated Surfaces with Application to Supersonic-tunnel Contour Correction written by Maurice Tucker and published by . This book was released on 1950 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: As an application of the method, the contour correction of supersonic nozzles for the effects of boundary-layer development is discussed from the requirement of continuity of mass flow and from the requirement of expansion- and shock-wave elimination.
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 Turbulent Shear Layers in Supersonic Flow by : Alexander J. Smits
Download or read book Turbulent Shear Layers in Supersonic Flow written by Alexander J. Smits and published by Springer Science & Business Media. This book was released on 2006-05-11 with total page 418 pages. Available in PDF, EPUB and Kindle. Book excerpt: A good understanding of turbulent compressible flows is essential to the design and operation of high-speed vehicles. Such flows occur, for example, in the external flow over the surfaces of supersonic aircraft, and in the internal flow through the engines. Our ability to predict the aerodynamic lift, drag, propulsion and maneuverability of high-speed vehicles is crucially dependent on our knowledge of turbulent shear layers, and our understanding of their behavior in the presence of shock waves and regions of changing pressure. Turbulent Shear Layers in Supersonic Flow provides a comprehensive introduction to the field, and helps provide a basis for future work in this area. Wherever possible we use the available experimental work, and the results from numerical simulations to illustrate and develop a physical understanding of turbulent compressible flows.
Book Synopsis Investigation of Supersonic Turbulent Boundary-layer Separation on a Compression Ramp by an Integral Method by :
Download or read book Investigation of Supersonic Turbulent Boundary-layer Separation on a Compression Ramp by an Integral Method written by and published by . This book was released on 1977 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis WADC Technical Report by : United States. Wright Air Development Division
Download or read book WADC Technical Report written by United States. Wright Air Development Division and published by . This book was released on 1961 with total page 1246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Turbulent Boundary Layer in an Adverse Pressure Gradient by : Emerick Manley Fernando
Download or read book Supersonic Turbulent Boundary Layer in an Adverse Pressure Gradient written by Emerick Manley Fernando and published by . This book was released on 1988 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Supersonic Turbulent Boundary Layer in a Moderate Adverse Pressure Gradient. Part I.A Detailed Description of the Experiment and Data Tabulation by : Walter B. Sturek
Download or read book An Experimental Investigation of the Supersonic Turbulent Boundary Layer in a Moderate Adverse Pressure Gradient. Part I.A Detailed Description of the Experiment and Data Tabulation written by Walter B. Sturek and published by . This book was released on 1970 with total page 129 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental measurements of the profile characteristics of the supersonic turbulent boundary layer in a region of zero pressure gradient and in a region of moderate adverse pressure gradient along the curved surface of an isentropic ramp model are reported. Detailed surveys of impact pressure, static pressure and total temperature were taken through the boundary layer and local values of wall shear stress were obtained using the Preston tube technique. The measurements were made in a supersonic wind tunnel for a nominal tunnel nozzle setting of Mach 3.5. The data are for an adiabatic wall with values of momentum thickness Reynolds number ranging from 19,000 to 42,000. The experiment is described in detail and the mean profile data are presented in tabular form. Fluctuation data obtained using constant temperature hot wire anemometry are presented for one station in the region of zero pressure gradient and for one station in the region of adverse pressure gradient. (Author).
Book Synopsis U.S. Government Research Reports by :
Download or read book U.S. Government Research Reports written by and published by . This book was released on 1964 with total page 2180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis WADC Technical Report by : United States. Wright Air Development Division
Download or read book WADC Technical Report written by United States. Wright Air Development Division and published by . This book was released on 1961 with total page 1246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Theoretical Face Pressure and Drag Characteristics of Forward-facing Steps in Supersonic Turbulent Boundary Layers by : D. K. Patel
Download or read book Theoretical Face Pressure and Drag Characteristics of Forward-facing Steps in Supersonic Turbulent Boundary Layers written by D. K. Patel and published by . This book was released on 1975 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1984 with total page 1278 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of a Supersonic Turbulent Boundary Layer in an Adverse Pressure Gradient by : Eva Dillner Fields
Download or read book Investigation of a Supersonic Turbulent Boundary Layer in an Adverse Pressure Gradient written by Eva Dillner Fields and published by . This book was released on 1977 with total page 252 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Centennial of Powered Flight by : G. M. Faeth
Download or read book Centennial of Powered Flight written by G. M. Faeth and published by AIAA. This book was released on 2003 with total page 400 pages. Available in PDF, EPUB and Kindle. Book excerpt: Read it! Click on the paper titles below for a FREE preview of the content. This book contains papers written by the most remarkable minds in the field of aerospace over the past 60 years. It contains unusually significant papers that have appeared in the "AIAA Journal" and its predecessors ("Journal of Aeronautical Sciences, Journal of Aerospace Sciences, ARS Journal, ARS Bulletin, Astronautics, Journal of the American Rocket Society, " and "Jet Propulsion").
Book Synopsis Fundamental Aspects of the Structure of Supersonic Turbulent Boundary Layers by : Alexander J. Smits
Download or read book Fundamental Aspects of the Structure of Supersonic Turbulent Boundary Layers written by Alexander J. Smits and published by . This book was released on 1988 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
