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An Approximate Solution For Compressible Axisymmetric Laminar Boundary Layers Including The Effects Of Transverse Curvature
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Book Synopsis An Approximate Solution for Compressible Axisymmetric Laminar Boundary Layers Including the Effects of Transverse Curvature by : Jay M. Solomon
Download or read book An Approximate Solution for Compressible Axisymmetric Laminar Boundary Layers Including the Effects of Transverse Curvature written by Jay M. Solomon and published by . This book was released on 1967 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt: An approximate momentum integral solution for the compressible axisymmetrix laminar boundary layer when transverse curvature effects are important is presented. Both finite and infinite inviscid Mach numbers are considered. Detailed comparisons with exact asymptotic solutions are given. The method is found, in many instances, to agree to leading order with the exact solutions as the transverse curvature becomes very large--a property that none of the existing approximate solutions for compressible flow possess. Some example calculations for a cone in supersonic and hypersonic flow are presented. Also, the method is applied to the hypersonic self-induced pressure problem for a cone. (Author).
Book Synopsis An Approximate Solution for Compressible Axisymmetric Laminar Boundary Layers Including the Effects of Transverse Curvature by : Jay M. Solomon
Download or read book An Approximate Solution for Compressible Axisymmetric Laminar Boundary Layers Including the Effects of Transverse Curvature written by Jay M. Solomon and published by . This book was released on 1967 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: An approximate momentum integral solution for the compressible axisymmetrix laminar boundary layer when transverse curvature effects are important is presented. Both finite and infinite inviscid Mach numbers are considered. Detailed comparisons with exact asymptotic solutions are given. The method is found, in many instances, to agree to leading order with the exact solutions as the transverse curvature becomes very large--a property that none of the existing approximate solutions for compressible flow possess. Some example calculations for a cone in supersonic and hypersonic flow are presented. Also, the method is applied to the hypersonic self-induced pressure problem for a cone. (Author).
Book Synopsis Axisymmetric Laminar Boundary Layers with Very Large Transverse Curvature by : Jay M. Solomon
Download or read book Axisymmetric Laminar Boundary Layers with Very Large Transverse Curvature written by Jay M. Solomon and published by . This book was released on 1967 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt: The compressible axisymmetric laminar boundary layer is considered for very large values of the transverse curvature parameter (roughly proportional to the ratio of the Mangler value of the boundary layer displacement thickness to the local cross-sectional radius of the body). Asymptotic expansions are constructed using the method of inner-outer expansions and verified by comparison with exact numerical similarity solutions. Both finite and hypersonic Mach number inviscid flow conditions are considered. The principal results are asymptotic formulas for skin friction, heat transfer, and boundary layer displacement thickness. Existing expansions, obtained by Wei, are found to be incorrect. The viscous pressure interaction near the vertex of a pointed axisymmetric body is treated within the framework of boundary layer theory and a tangent-cone approximation. (Author).
Book Synopsis Axisymmetric Laminar Boundary Layers with Very Large Transverse Curvature by : Jay M. Solomon
Download or read book Axisymmetric Laminar Boundary Layers with Very Large Transverse Curvature written by Jay M. Solomon and published by . This book was released on 1967 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt: The compressible axisymmetric laminar boundary layer is considered for very large values of the transverse curvature parameter (roughly proportional to the ratio of the Mangler value of the boundary layer displacement thickness to the local cross-sectional radius of the body). Asymptotic expansions are constructed using the method of inner-outer expansions and verified by comparison with exact numerical similarity solutions. Both finite and hypersonic Mach number inviscid flow conditions are considered. The principal results are asymptotic formulas for skin friction, heat transfer, and boundary layer displacement thickness. Existing expansions, obtained by Wei, are found to be incorrect. The viscous pressure interaction near the vertex of a pointed axisymmetric body is treated within the framework of boundary layer theory and a tangent-cone approximation. (Author).
Book Synopsis Comparison of a First-order Treatment of Higher-order Boundary-layer Effects with Second-order Theory and Experimental Data by : Clark Houston Lewis
Download or read book Comparison of a First-order Treatment of Higher-order Boundary-layer Effects with Second-order Theory and Experimental Data written by Clark Houston Lewis and published by . This book was released on 1968 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt: The axisymmetric nonsimilar compressible laminar boundary-layer equations including approximate transverse curvature terms were modified to treat inviscid external vorticity, slip and temperature jump as first-order quantities, and this is referred to as the first-order treatment. The effects of boundary-layer displacement were also treated. Primary interest was in predicting experimentally measurable quantities over the entire body length of nonanalytic shapes, and the analysis was not confined to the nose or stagnation region. A review is included of second-order boundary-layer theory and of recent developments in the numerical solution of second-order boundary-layer effects. Comparisons of predicted displacement-induced pressure distributions, heat-transfer distributions and zero-lift drag were made with results from second-order boundary-layer theory and experimental data for a spherically blunted 9-deg half-angle cone at free-stream Mach numbers of 9 and 18. At moderate to high Reynolds numbers, the comparisons showed good agreement between first- and second-order predictions and experimental results for drag and heat-transfer distributions; however, poor agreement was found between predicted and experimental displacement-induced pressure distributions. At low Reynolds numbers, both first- and second-order treatments substantially overpredicted the zero-lift drag. The range of applicability of the theories was established for the conditions treated by inspection of the numerical results and by comparison of the numerical results with experimental zero-lift drag data. (Author).
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 1991 with total page 1460 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Book Synopsis Solution of the General Boundary-layer Equations for Compressible Laminar Flow, Including Transverse Curvature by : Darwin W. Clutter
Download or read book Solution of the General Boundary-layer Equations for Compressible Laminar Flow, Including Transverse Curvature written by Darwin W. Clutter and published by . This book was released on 1963 with total page 0 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 1968 with total page 828 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis U.S. Government Research and Development Reports Index by :
Download or read book U.S. Government Research and Development Reports Index written by and published by . This book was released on 1968 with total page 1492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Transverse Curvature Effect in Compressible Axially-symmetric Laminar Boundary Layer Flow Including the Effects of Pressure Gradient by : David Elliott
Download or read book The Transverse Curvature Effect in Compressible Axially-symmetric Laminar Boundary Layer Flow Including the Effects of Pressure Gradient written by David Elliott and published by . This book was released on 1954 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Solutions of the Laminar Compressible Boundary-layer Equations with Transpiration which are Applicable to the Stagnation Regions of Axisymmetric Blunt Bodies by : John T. Howe
Download or read book Solutions of the Laminar Compressible Boundary-layer Equations with Transpiration which are Applicable to the Stagnation Regions of Axisymmetric Blunt Bodies written by John T. Howe and published by . This book was released on 1959 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Announcements by :
Download or read book Government Reports Announcements written by and published by . This book was released on 1975-05-16 with total page 226 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1974 with total page 592 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Solution to the Binary Diffusion Laminar Boundary Layer Equations Including the Effect of Second-order Transverse Curvature by : N. A. Jaffe
Download or read book Solution to the Binary Diffusion Laminar Boundary Layer Equations Including the Effect of Second-order Transverse Curvature written by N. A. Jaffe and published by . This book was released on 1966 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents a numerical method for solving the binary diffusion laminar boundary-layer equations. The differential equations of continuity, momentum, energy, and species diffusion are solved simultaneously for two-dimensional or axisymmetric flow. For the case of axisymmetric flow the second-order transverse curvature terms appearing in the equations are retained. Relations for mixture fluid properties as functions of local conditions in the boundary layer are developed and used in obtaining solutions to the equations. The mixtures considered in the investigation are He - air, Ar - air, and CO2 - air. Solutions to the equations are given for flow of a pure air free stream over a 9 degree half angle cone at a free stream Mach number of 10 and free stream Reynolds number, based on cone slant length of 940. The initial section of the cone is solid and mass injection is initiated at a location downstream of the tip. Results are presented and compared for calculations both including and neglecting the second-order transverse curvature effect. (Author).
Book Synopsis U.S. Government Research & Development Reports by :
Download or read book U.S. Government Research & Development Reports written by and published by . This book was released on 1969 with total page 1208 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis U. S. Government Research and Development Reports by :
Download or read book U. S. Government Research and Development Reports written by and published by . This book was released on 1969 with total page 1214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Bibliography of Scientific and Industrial Reports by :
Download or read book Bibliography of Scientific and Industrial Reports written by and published by . This book was released on 1969 with total page 1240 pages. Available in PDF, EPUB and Kindle. Book excerpt:
