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Studies Of Three Dimensional Boundary Layers On Bodies Of Revolution Iii Cones At Incidence In Supersonic Flow
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Book Synopsis Studies of Three-Dimensional Boundary Layers on Bodies of Revolution. III. Cones at Incidence in Supersonic Flow by : Tuncer Cebeci
Download or read book Studies of Three-Dimensional Boundary Layers on Bodies of Revolution. III. Cones at Incidence in Supersonic Flow written by Tuncer Cebeci and published by . This book was released on 1982 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation is carried out into the properties of a nonsimiliar boundary layer on a cone at incidence with special reference to the flow near the leeside line of symmetry. The nonsimilarity is induced by allowing suction near the vertex of the cone and the external velocity is given by supersonic inviscid theory. The principal new results of the theory may be expressed in terms of a parameter -k, which is approximately equivalent to the angle of attack of the cone. Three ranges of k have been identified. For small negative values of k, the three-dimensional boundary layer on the cone is smooth everywhere and, once the suction is removed, rapidly approaches a semi-similarity form as the distance from the vertex increases. For more negative values of k the boundary layer is not smooth near the leeside of the cone but can be computed everywhere. The nature of this singularity is partially explained in terms of a collision phenomenon. If k decreases further, separation occurs in computations from the windward side of the cone. The solution develops a singularity along this line provided sufficient care is taken in the calculations. An apparent nonuniqueness in the solution prevents integration from the leeside over the remainder of the region of accessibility.
Book Synopsis Three-Dimensional Boundary Layers on Bodies of Revolution at Incidence by : V. C. Patel
Download or read book Three-Dimensional Boundary Layers on Bodies of Revolution at Incidence written by V. C. Patel and published by . This book was released on 1978 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report summarizes the objectives and accomplishments of an experimental and theoretical investigation of the boundary layer development on bodies of revolution at incidence. The results of the flow visualization studies in laminar flow, detailed measurements in a turbulent boundary layer, and calculations of laminar as well as turbulent boundary layers using two different numerical schemes and turbulence models are reviewed to emphasize the important characteristics of separation in three dimensions.
Book Synopsis Three-dimensional Laminar Boundary-layer Analysis of Upwash Patterns and Entrained Vortex Formation on Sharp Cones at Angle of Attack by : John C. Adams (Jr.)
Download or read book Three-dimensional Laminar Boundary-layer Analysis of Upwash Patterns and Entrained Vortex Formation on Sharp Cones at Angle of Attack written by John C. Adams (Jr.) and published by . This book was released on 1971 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: Application of three-dimensional inviscid and viscous (laminar boundary layer) analyses for cold wall hypersonic flows over sharp cones at incidence is presented relative to experimental data, showing surface upwash angles and entrained vortex formation leading to crossflow-induced boundary-layer transition. Three-dimensional neutral inviscid stability theory for stationary disturbances is used to calculate the angular orientation of the entrained vortices in the boundary layer while a maximum crossflow Reynolds number concept is applied for correlation of the onset to vortex formation due to crossflow instability.
Book Synopsis Boundary Layer Transition at Supersonic Speeds by : E. R. Van Driest
Download or read book Boundary Layer Transition at Supersonic Speeds written by E. R. Van Driest and published by . This book was released on 1961 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.
Book Synopsis Studies on Three-Dimensional Boundary Layers on Bodies of Revolution. I. Nose Separation by : Tuncer Cebeci
Download or read book Studies on Three-Dimensional Boundary Layers on Bodies of Revolution. I. Nose Separation written by Tuncer Cebeci and published by . This book was released on 1978 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: The laminar boundary-layer development near the nose of a body of revolution and a two-dimensional airfoil is investigated until the onset of leading-edge separation. This is accomplished through the use of a coordinate transformation which eliminates any geometrical singularity at the nose in the governing boundary-layer equations. The resulting equations are examined by both asymptotic and numerical means. Comparable cases for the three-dimensional body of revolution and the two-dimensional airfoil are given and similarities as well as differences are discussed. (Author).
Book Synopsis Preliminary Surveys of the Three Dimensional Boundary Layer on a Yawed, Spinning Body of Revolution by : Walter B. Sturek
Download or read book Preliminary Surveys of the Three Dimensional Boundary Layer on a Yawed, Spinning Body of Revolution written by Walter B. Sturek and published by . This book was released on 1975 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental measurements of the three dimensional boundary layer on a yawed, spinning tangent-ogive-cylinder model in supersonic flow are reported. The measurements were made using a flattened total head probe at one axial station near the base of the model for 10 azimuthal stations about the circumference. The test conditions were: M = 3, angle of attack = 4 deg, omega = 0 and 10,000 RPM. The trends observed in comparing measurements with and without the model spinning were: (1) the boundary layer is more thick and less full where surface spin opposes the crossflow velocity; and (2) the boundary layer is less thick and more full where surface spin is in the same direction as the crossflow velocity. (Author).
Book Synopsis Three-dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack by : M. J. Abbett
Download or read book Three-dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack written by M. J. Abbett and published by . This book was released on 1968 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt: The solution for the steady three-dimensional inviscid flow about supersonic blunt cones at angle of attack is obtained by coupling a direct time-dependent solution for the subsonic portion of the shock layer with steady state numerical afterbody solution. An outline is given covering the coupling scheme and the use of the resulting Fortran computer code.
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 1992 with total page 1572 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of Three-Dimensional Boundary Layers on Bodies of Revolution at Incidence by : Tuncer Cebeci
Download or read book Calculation of Three-Dimensional Boundary Layers on Bodies of Revolution at Incidence written by Tuncer Cebeci and published by . This book was released on 1978 with total page 175 pages. Available in PDF, EPUB and Kindle. Book excerpt: The laminar three-dimensional boundary layer on a body of revolution at incidence is investigated using two methods. In the first, the standard equations are solved numerically using the Keller box scheme. The second method solves a set of equations, which contain the standard equations, derived from the assumption that crossflow gradients may be important. Since these equations are elliptic in the crossflow plane, an ADI procedure is used for their solution. In regions where there is no crossflow reversal, both methods yield the same results. However, differences appear in regions where the crossflow is not unidirectional. Reasons for this discrepancy are discussed and the relative merits of each procedure identified. (Author).
Book Synopsis Three-dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack by : G. Moretti
Download or read book Three-dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack written by G. Moretti and published by . This book was released on 1968 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Comparisons are made between the cylindrical and polar coordinate system used in determining the three-dimensional shock layer flow over the nose region of a blunted supersonic vehicle. Jusfification for the development of a polar coordinate system is given and an outline for such development is presented. Results from the polar coordinate system are given as is the limiting useful range.
Book Synopsis Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds by : William A. Cassels
Download or read book Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds written by William A. Cassels and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer transition by the sublimation and impact-pressure techniques and force tests have been performed on three Haack-Adams bodies of revolution of fineness ratios 7, 10, and 13 at zero angle of attack for free-stream Mach numbers of 2.00, 2.75, and 4.63 and a range of Reynolds numbers based on model length of 6 to 15 X 10(to the 6 power) with and without a roughness strip. The grit method of inducing turbulence was found to provide for a nearly complete turbulent flow over the models at the lower Mach numbers and higher Reynolds numbers considered in this study while the amount of trip drag was less than 8 percent of the model drag with transition fixed. A method of interpreting sublimation data was discussed and used and the results compared well with the impact-pressure results.
Author :North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel Publisher : ISBN 13 : Total Pages :62 pages Book Rating :4.0/5 ( download)
Book Synopsis Hypersonic Boundary Layers and Flow Fields by : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel
Download or read book Hypersonic Boundary Layers and Flow Fields written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel and published by . This book was released on 1968 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Annual Index by :
Download or read book Government Reports Annual Index written by and published by . This book was released on 1983 with total page 1092 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three-Dimensional Supersonic Viscous Flow Over a Cone at Incidence by : A. Lin
Download or read book Three-Dimensional Supersonic Viscous Flow Over a Cone at Incidence written by A. Lin and published by . This book was released on 1981 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: The viscous supersonic flow over a sharp cone at incidence is examined numerically with a coupled strongly implicit algorithm for the properties in the plane normal to the cone axis. The Navier-Stokes equations are considered in a boundary layer-like or parabolized manner and global relaxation is considered for the pressure interaction. It is shown that departure effects can be effectively eliminated by forward differencing for the axial pressure gradient. Moreover, this approximation retains the implicit free pressure interaction required for geometries where axial flow separation is possible. (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 1963 with total page 964 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Annual Index: Keyword A-L by :
Download or read book Government Reports Annual Index: Keyword A-L written by and published by . This book was released on 1987 with total page 1260 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis OAR Cumulative Index of Research Results by :
Download or read book OAR Cumulative Index of Research Results written by and published by . This book was released on 1967 with total page 1264 pages. Available in PDF, EPUB and Kindle. Book excerpt:
