Download or read book Intersecting Shock Wave Turbulent Boundary Layer Interactions at Mach 8 3 written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-10-28 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental data for two three-dimensional intersecting shock-wave/turbulent boundary-layer interaction flows at Mach 8.3 are presented. The test bodies, composed of two sharp fins fastened to a flat-plate test bed, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface pressure and heat transfer distributions as well as mean flow-field surveys both in the undisturbed and interaction regimes. The data are presented in a convenient form to be used to validate existing or future computational models of these hypersonic flows. The data are also on a 3.5-inch diskette included and are available through E-mail. Kussoy, M. I. and Horstman, K. C. Ames Research Center...
Download or read book Three dimensional Shock Wave turbulent Boundary Layer Interactions at Mach 6 written by C. Herbert Law and published by . This book was released on 1975 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental results of an investigation of the three-dimensional interaction between a skewed shock wave and a turbulent boundary layer are presented. Surface pressure and heat transfer distributions and oil flow photographs were obtained at a freestream Mach number of 5.85 and two Reynolds numbers of ten and twenty million per foot. The model configuration consisted of a shock generator mounted perpendicularly to a flat plate. The shock generator leading edge was sharp and nonswept and intersected the flat plate surface about 8.5 inches downstream of the flat plate leading edge. The shock generator surface was 7.55 inches long and 3 inches high and its angle to the freestream flow was adjusted from 4 to 20 degrees. The generated shock waves were of sufficient strength to produce turbulent boundary layer separation on the flat plate surface.
Download or read book On 3 D Shock Wave turbulent Boundary Layer Interactions at Mach 4 written by Datta Gaitonde and published by . This book was released on 1996 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Shock Wave Boundary Layer Interactions written by Holger Babinsky and published by Cambridge University Press. This book was released on 2011-09-12 with total page 481 pages. Available in PDF, EPUB and Kindle. Book excerpt: Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
Download or read book Three dimensional Shock Wave turbulent Boundary Layer Interactions at Mach 6 written by C. Herbert Law and published by . This book was released on 1975 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 3 D Shock Wave turbulent Boundary Layer Interaction for a 20 Degree Sharp Fin at Mach 3 written by Bryon Lorne Shapey and published by . This book was released on 1987 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experiments on the Interaction with a Turbulent Boundary Layer of a Skewed Shock Wave of Variable Strength at Mach 2 5 written by L. Michael Freeman and published by . This book was released on 1975 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report covers an experimental study of the interaction of a skewed shock wave of variable strength with a turbulent boundary layer at a working Mach number of 2.5. The skewed shock wave was generated by a vertical wedge whose angle was varied in increments of 1 degree or less between 6 and 18 degrees in order to cover the spectrum of interaction from below incipient to widespread separation. Measurements include pressure distributions and oil flow photographs. The incipient separation angle was found to be between 71/2 and 8 degrees. For large wedge angles there is the appearance in the oil flow photographs of an inflection within the separated region, suggesting the possible approach to a secondary separation. The extent of separation is relatively small for angles up to 10 degrees, but grows more rapidly for larger angles. (Author).
Download or read book Flow Field Measurements in a Crossing Shock Wave turbulent Boundary Layer Interaction at Mach 3 written by Jason T. Lachowicz and published by . This book was released on 1992 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Numerical Computations of Turbulence Amplification in Shock Wave Interactions written by Thomas A. Zang and published by . This book was released on 1983 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Interaction Between Shock Waves and Turbulent Or Transitional Boundary Layers at Mach Number 3 written by Edelbert Eugene Irish and published by . This book was released on 1957 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Oblique Shock Wave Turbulent Boundary Layer Interactions in Three Dimensions at Mach 3 written by B. Oskam and published by . This book was released on 1978 with total page 181 pages. Available in PDF, EPUB and Kindle. Book excerpt: The second phase of a detailed experimental investigation has been carried out on the interaction between oblique shock waves and turbulent boundary layers in three dimensions. The present work extends the original region of study of the shock wave interaction area towards the streamwise corner between the shock generator and the test wall. The purpose of this report is to present the experimental data in tabulated form. The tabulations include both surface data such as heat transfer and static pressure as well as detailed flow field surveys of pitot pressure, flow angularity, static pressure and total temperature.
Download or read book Oblique Shock Wave Turbulent Boundary Layer Interactions in Three Dimensions at Mach 3 written by B. Oskam and published by . This book was released on 1976 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study, thoroughly documenting the flow field and surface data resulting from the three-dimensional interaction of a shock wave, a shock generator and a high Reynolds number turbulent boundary layer, is described. Detailed surface static pressure data and heat transfer measurements are presented for 7 shock generator deflection angles ranging from 2 to 14 deg. in 2 deg. increments. The test conditions consist of a free stream Reynolds number per inch of 1.6 million, a near adiabatic wall temperature and ambient stagnation temperature. In addition to the surface data detailed flow field surveys have been conducted of time-averaged variables including flow angularity, pitot pressure, static pressure and total temperature at 2 shock generator deflection angles of 4 and 10 degrees. Detailed discussions of the experimental techniques are given which include a complete set of error estimates of the various types of data. Finally the data are presented in graphical form which may be used to analyse the problem under consideration. (Author).
Download or read book A Study of Normal Shock Wave Turbulent Boundary Layer Interactions at Mach Numbers of 1 3 1 4 and 1 5 written by W. G. Sawyer and published by . This book was released on 1982 with total page 155 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of a study of seven flows involving the interaction between a normal shock wave and a two-dimensional turbulent boundary layer. The measurements were made at free-stream Mach numbers of 1.3, 1.4 and 1.5 and at Reynolds numbers based on an effective streamwise run of 10 to 30-million. The results were obtained from comprehensive traverses with both pilot and static probes. Standard boundary-layer integral parameters based on wall and measured static pressures are presented, together with velocity profiles and the Mach number distribution over the interaction region. An investigation has been made of the 'law of the wall' and the 'law of the wake' under the influence of strong normal pressure gradients.
Download or read book Three dimensional Shock Wave turbulent Boundary Layer Interaction for a 20 Degrees Sharp Fin at Mach 3 written by B. Shapey and published by . This book was released on 1987 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theoretical Investigation of 3 D Shock Wave Turbulent Boundary Layer Interactions written by Doyle Knight and published by . This book was released on 1988 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: This research describes continuing efforts in the analysis of 3-D shock wave turbulent boundary layer interactions. A significant research activity in 3-D hypersonic shock turbulent interactions is initiated to further develop and validate the theoretical model. The quasiconical free interaction principle is examined by simulation of two geometries -17.5 deg sharp fin and (30,60) swept compression corner (Mach 3) - selected to obtain similar shock strengths. The comparison with experimental data is good. It is confirmed that the differences caused by the particular geometry of the model appear only behind the inviscid shock wave. Continuing research on 3-D turbulent interaction control is focused on the effect of bleed and the simulation of flows past the double-fin configuration. The effect of suction is examined on a strong (fin angle=20 deg, Mach 3) and a weak interaction (8 deg, Mach 3). The overall effect of bleed is remarkably modest. Two double-fin configurations (4 x 4 and 8 x 8, Mach 3) are simulated. A study of the computed flowfield indicates that the first is a weak interaction. In contrast, the 8 x 8 configuration displays an interesting separated flowfield. An analysis of viscous and inviscid effects in a sharp fin and a swept corner flow indicates that the physics of both geometries are governed primarily by inviscid (pressure) effects. Viscous effects are of lower magnitude but are not restricted to the sublayer region. High speed flows; Viscous inviscid interactions; Boundary layer interactions; Computational fluid dynamics; Navier stokes equations; Turbulence.(mjm).
Download or read book Investigation of Small Surface Protuberances Upstream of Turbulent Boundary Layer Separation written by Robert H. Korkegi and published by . This book was released on 1976 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theoretical Investigation of 3 D Shock Wave Turbulent Boundary Layer Interactions written by and published by . This book was released on 1992 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: The research concerns the understanding of 3-D shock wave/turbulent boundary-layer interactions. The research effort during the current period focused on the following areas: (a) the 3-D double fin (crossing shock) interaction at Mach 8.3 for symmetric 15 deg fins, (2) the 3-D crossing shock interaction at Mach 4 for symmetric 15 deg fins, and (3) the 3-D tripe (triple shock) interaction at Mach 8.3 for 10 deg fins.
