Download or read book Results of Calculation of the Boundary Layer of Blunted Cones in Supersonic Flow written by A. L. ANKUDINOV and published by . This book was released on 1966 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: The paper presents the results of the calculation of the boundary layer of spherically blunted cones in supersonic airflow for a given (constant) wall temperature and for a thermally insulated wall.
Download or read book Roll Damping Derivative Calculations for Spinning Sharp and Blunt Cones in Supersonic and Hypersonic Flow written by and published by . This book was released on 1979 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The boundary-layer equations in a Crocco variables form have been numerically solved for flow over spinning sharp and blunt cones at zero incidence to supersonic and hypersonic streams. Both laminar and turbulent flows have been treated, and for the blunt cases swallowing of the inviscid entropy layer by the boundary layer has been considered. The item of primary interest is roll damping, and results of a parametric study involving Mach number, Reynolds number, cone angle, and bluntness ratio are presented. Limited comparisons with experimental data and another method of computation are also presented. (Author).
Download or read book Laminar Boundary Layer on a Circular Cone in Supersonic Flow at a Small Angle of Attack written by Franklin K. Moore and published by . This book was released on 1951 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt: The laminar boundary layer on a circular cone at angle of attack to a supersonic stream is discussed. A perturbation analysis was made to show the influence of a small angle of attack on such boundary layer quantities as skin friction, boundary-layer thickness, viscous lift, drag, and pitching moment.
Download or read book Boundary Layer Flows Over Sharp and Spherically Blunted Cones at Angle of Attack to Supersonic Nonuniform Free Streams Volume I Analysis and Results written by Michael C. Frieders and published by . This book was released on 1973 with total page 131 pages. Available in PDF, EPUB and Kindle. Book excerpt: Methods have been developed to solve the problem of laminar boundary layers on sharp and spherically blunt cones at angle of attack to nonuniform supersonic free streams. A three-dimensional boundary-layer solution is used to solve sharp cone problems and the afterbody of blunt cone problems. An axisymmetric boundary-layer solution is used to solve the axisymmetric region of blunt cones. An existing implicit finite-difference numerical scheme was used to solve both the axisymmetric and three-dimensional boundary-layer equations. A modified inverse method for solving the inviscid flow field is used to provide edge properties for the axisymmetric region of blunt cones. Normalized skin friction and heat transfer coefficients for a sharp cone in two-dimensional shear flow increase downstream relative to conical flow values. (Modified author abstract).
Download or read book The Drag of Slightly Blunted Slender Cones written by W. Carson Lyons (Jr.) and published by . This book was released on 1968 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer program is presented for calculating the various components comprising the total drag coefficient for slightly blunted slender cones. The program is applicable for either the case of a completely laminar boundary layer or where transition occurs on the cone. Weak viscous interaction effects are taken into account. Local flow properties which exist at the outer edge of the boundary layer along the cone are also computed. (Author).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1986 with total page 1108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Roll Damping Derivative Calculations for Spinning Sharp and Blunt Cones in Supersonic and Hypersonic Flow written by and published by . This book was released on 1979 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The boundary-layer equations in a Crocco variables form have been numerically solved for flow over spinning sharp and blunt cones at zero incidence to supersonic and hypersonic streams. Both laminar and turbulent flows have been treated, and for the blunt cases swallowing of the inviscid entropy layer by the boundary layer has been considered. The item of primary interest is roll damping, and results of a parametric study involving Mach number, Reynolds number, cone angle, and bluntness ratio are presented. Limited comparisons with experimental data and another method of computation are also presented. (Author).
Download or read book Laminar and Turbulent Boundary Layers on Slightly blunted Cones at Hypersonic Speeds written by R. E. Wilson and published by . This book was released on 1966 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: A momentum-integral method for calculating the boundary-layer growth on slightly-blunted cones has been given in a previous paper by the writer. The method, which was applied to cones with fully laminar flow, is extended in the present paper to turbulent flow. In addition: (1) transition data on cones at hypersonic speeds are examined to show the great effect of slight nose blunting on interpretation of the results, (2) agreement between measured and calculated cone drag coefficients for fully laminar flow is demonstrated, and (3) turbulent friction and boundary-layer thickness calculations are shown to agree with the limited amount of ballistics range data which are available.
Download or read book Effects of Cone Angel Mach Number and Nose Blunting on Transition at Supersonic Speeds written by K. R. Czarnecki and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Turbulent Boundary Layer on a Yawed Cone in a Supersonic Stream written by Willis H. Braun and published by . This book was released on 1959 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The momentum integral equations are derived for the boundary layer on an arbitrary curved surface, using a streamline coordinate system. Computations of the turbulent boundary layer on a slightly yawed cone are made for a Prandtl number of 0.729, wall to free-stream temperature ratios of 1/2, 1, and 2, and Mach numbers from 1 to 4. Deflection of the fluid in the boundary layer from outer stream direction, local friction coefficient, displacement surface, lift coefficient, and pitching-moment coefficient are presented.
Download or read book Laminar and Turbulent Boundary Layers of Slightly blunted Cones at Hypersonic Speeds written by W. E. Wilson and published by . This book was released on 1966 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: A momentum-integral method for calculating the boundary-layer growth on slightly-blunted cones has been given in a previous paper by the writer. The method, which was applied to cones with fully laminar flow, is extended in the present paper to turbulent flow. In addition: (1) transition data on cones at hypersonic speeds are examined to show the great effect of slight nose blunting on interpretation of the results, (2) agreement between measured and calculated cone drag coefficients for fully laminar flow is demonstrated, and (3) turbulent friction and boundary-layer thickness calculation are shown to agree with the limited amount of ballistics range data which are available.
Download or read book A Review of High speed Convective Heat transfer Computation Methods written by Michael E. Tauber and published by . This book was released on 1989 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Application of the Method of Characteristics for the Calculation of Flow Around Blunted Cones by a Supersonic Stream of Air written by R. A. Gzhelyak and published by . This book was released on 1968 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: This article deals with the application of the method of characteristics to calculations of a supersonic region of the flow near a blunt body, and is based on the available data obtained from the detailed analyses of dissociation and ionization processes taking place behind a shock wave. Boundary conditions on the body and shock wave are used in the form which coincides with the case of a perfect gas with constant heat capacities, because all physicochemical processes are considered frozen when passing through a shock front. Calculations of the flow field between the body and shock wave were carried out progressively by regions bounded by the reflected characteristics. The results of the calculations of the air flow past blunt cones are presented as an illustrative example and are compared with those for an equilibrium flow. The comparison of pressure and density distributions along blunt cones is presented in graphical form.
Download or read book Aerodynamics of Bodies of Revolution written by Nikolaĭ Fedorovich Krasnov and published by Elsevier Publishing Company. This book was released on 1970 with total page 930 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive technical treatise is provided on the aerodynamics of bodies of revolution from transonic to hypersonic speeds, covering all aspects of the subject, including transonic flow, linearized supersonic flow, Newtonian flow, rarefield gas and free-molecule flow, skin friction, heat transfer, and mass transfer. This English translation of a unique Russian textbook is provided with some corrections, references for all sources the editor could identify, redrawn figures, and an editor's introduction to each chapter summarizing and referencing pertinent material that has appeared since 1964, when the second edition was published. Krasnov's general approach assumes knowledge of the basic gas dynamic equations and applies them to solve aerodynamic problems. All important methods and techniques in modern aerodynamic theory are developed, with the aim of presenting practical methods for solving engineering problems. Results are usually given in the form of working equations, graphs, tables, or detailed sequential calculation methods. (Author).
Download or read book Laminar Boundary Layer on a Cone in Supersonic Flow with Uniform Mass Transfer written by Paul A. Libby and published by . This book was released on 1966 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A solution for the laminar boundary layer on a cone with uniform mass transfer is obtained. The velocity field is found for either suction or injection but the related solution for the energy field is subject to an energy balance at the exposed surface and is therefore valid only for injection. This latter solution is equally applicable to certain species fields as well. The present results along with those presented previously for the two-dimensional case permit a comparison of the effect of injection on boundary layers over two-dimensional and conical surfaces.
Download or read book Boundary Layer Development in Supersonic Shear Flow written by Ruth H. Rogers and published by . This book was released on 1960 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The development of the boundary layer on the surface of a blunt cone has been investigated. Experimental results are presented for cones having a 15 degree included angle and a tip radius varying from less than a thousandth of an inch to about half an inch. The cones were placed in streams whose undisturbed Mach numbers were 3.12 and 3.81. It was found that the position of transition to turbulence moved downstream as the tip radius was increased when its distance from the tip was greater than about 100 times the tip radius. When the position of transitions was nearer the tip than this, it moved upstream as the tip radius increased. Pitot traverses of the boundary layer were made, and it was found that transition occurred (in a given stream) at a constant value of the Reynolds number, R Delta 2, which is based on conditions at the edge of the boundary layer, and on its momentum thickness. It is demonstrated that, although the Reynolds number per inch near the tip of a blunt cone is smaller than that on a sharp cone, the momentum thickness on a blunt cone is greater than would be expected on a sharp cone. Some preliminary theoretical results are quoted which predict qualitatively all the above results. The assumptions made in this theory remain, however, unjustified. (Author).
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.
