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Turbulent Supersonic Boundary Layer Flow In An Adverse Pressure Gradient Including The Effects Of Mass Bleed
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Book Synopsis Turbulent Supersonic Boundary Layer Flow in an Adverse Pressure Gradient Including the Effects of Mass Bleed by : David William Mayer
Download or read book Turbulent Supersonic Boundary Layer Flow in an Adverse Pressure Gradient Including the Effects of Mass Bleed written by David William Mayer and published by . This book was released on 1977 with total page 320 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 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 Supersonic Turbulent Boundary-layer Flows with Mass Injection Through Slots And/or Porous Walls by : Alvin L. Murray
Download or read book Supersonic Turbulent Boundary-layer Flows with Mass Injection Through Slots And/or Porous Walls written by Alvin L. Murray and published by . This book was released on 1975 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: An implicit finite-difference method was used to solve the compressible boundary-layer equations, and to study the effects of mass transfer through porous plates, slots, and a combination of the two. The effects of the external pressure field were also included by using a global pressure interaction scheme. Two different eddy viscosity models were used for the slot and slot-porous combination cases: one was a two-layer model with inner and outer laws, and the other was a multi-layer model with as many as five separate layers. Results of the present method were compared with experimental data at a Mach number of 2.8. Comparisons of the skin friction reduction and Mach number profiles gave good to excellent agreement. Pressure interaction had little effect on the slot injection skin friction but increased the skin friction of the porous and slot-porous combination markedly.
Book Synopsis Pressure Gradient Effects on Supersonic Boundary Layer Turbulence by : A. J. Laderman
Download or read book Pressure Gradient Effects on Supersonic Boundary Layer Turbulence written by A. J. Laderman and published by . This book was released on 1979 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of mean flow profiles at several streamwise locations in a supersonic turbulent boundary layer growing under a continuous adverse pressure gradient are reported. Tests were performed at a freestream Mach number of 3, for an adiabatic wall, using two curved ramps designed to produce constant pressure gradient flows. The velocity profile data, when transformed to incompressible coordinates, are in good agreement with Coles universal 'wall-wake' velocity profile and they indicate that the boundary layer is in local equilibrium and essentially independent of upstream history. In addition, the Coles wake parameters and Clauser shape factors, characterizing the transformed profiles, are in accord with the results of low speed correlations of adverse pressure gradient flows. The turbulent transport terms were extracted from the mean flow field data and indicate that for a given ramp, the profile of turbulent shear stress normalized by the wall shear, versus distance from the surface, normalized by the local boundary thickness, is severely distored by the pressure gradient although it is apparently insensitive to local conditions.
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:
Book Synopsis An Experimental Investigation of Turbulent Supersonic Boundary Layer Flow in an Adverse Pressure Gradient by : Edward Gootzait
Download or read book An Experimental Investigation of Turbulent Supersonic Boundary Layer Flow in an Adverse Pressure Gradient written by Edward Gootzait and published by . This book was released on 1976 with total page 322 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of a Supersonic Turbulent Boundary Layer with Adverse Pressure Gradient by : Chad S. Hale
Download or read book Experimental Investigation of a Supersonic Turbulent Boundary Layer with Adverse Pressure Gradient written by Chad S. Hale and published by . This book was released on 1995 with total page 280 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 An Application of the Chapman-Korst Theory to Supersonic Nozzle-afterbody Flows by : R. C. Bauer
Download or read book An Application of the Chapman-Korst Theory to Supersonic Nozzle-afterbody Flows written by R. C. Bauer and published by . This book was released on 1977 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: A Chapman-Korst-type analysis has been developed for estimating the bulk base flow properties of nozzle-afterbody configurations operating at supersonic speeds. The analysis includes the effects of both initial boundary layers, dissimilar thermodynamic properties of both streams, and a third base bleed gas. The inviscid portions of the jet and external flow are computed by the method of characteristics. The turbulent mixing analysis uses the turbulent kinetic energy method to determine the coefficient in a Prandtl-type eddy viscosity model. The empirical coefficients in the turbulent kinetic energy formulation are those developed for the turbulent mixing of jet flows. A new analytical model of the recompression process has been developed that eliminates the need for an empirical recompression factor to determine the stagnating streamline. The analysis is evaluated by comparing with experimental data for Mach 2.0 flow over a two-dimensional blunt base with hydrogen bleed, a two-dimensional backward-facing step and a hot and a cold rocket nozzle-afterbody configuration. Usually the theoretical base pressure is greater than experimental base pressure, indicating the mixing rate is too small. However, the recompression analysis predicts reasonable values of the recompression factor. (Author).
Book Synopsis Effect of Pressure Gradients on Plate Response and Radiation in a Supersonic Turbulent Boundary Layer by :
Download or read book Effect of Pressure Gradients on Plate Response and Radiation in a Supersonic Turbulent Boundary Layer written by and published by . This book was released on 1997 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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 The Effects of an Adverse Pressure Gradient on the Behavior of a Flat Plate Supersonic Turbulent Boundary Layer by : E.M. Fernando
Download or read book The Effects of an Adverse Pressure Gradient on the Behavior of a Flat Plate Supersonic Turbulent Boundary Layer written by E.M. Fernando and published by . This book was released on 1987 with total page 12 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 Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer by : Robert L. P. Voisinet
Download or read book Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer written by Robert L. P. Voisinet and published by . This book was released on 1973 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).
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:
