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Thrust Nozzle Optimization Including Boundary Layer Effects
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Book Synopsis Thrust Nozzle Optimization Including Boundary Layer Effects by : M. Peter Scofield
Download or read book Thrust Nozzle Optimization Including Boundary Layer Effects written by M. Peter Scofield and published by . This book was released on 1967 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt: An optimization analysis, a numerical method, and a computer program for the design of optimum thrust nozzles including boundary layer effects are presented. The analysis is based on the assumptions that the flow is homentropic and that the boundary layer is thin. The problem is formulated to maximize the pressure thrust integral along the supersonic wall contour for a general isoperimetric constraint. The results of the optimization analysis are a set of hyperbolic partial differential equations for determining the Lagrange multipliers in the region of interest, and a set of algebraic equations for determining the initial and boundary conditions for these multipliers on the boundaries of the region. The numerical method employes a simplified relaxation technique which, it is felt, will encourage the use of this general design technique. A preliminary parametric study was conducted to determine the possible percent thrust improvement that can be obtained by the inclusion of the boundary layer effects. (Author).
Book Synopsis Thrust Nozzle Optimization for Non-Equilibrium, Chemically Reacting Flows Including Boundary Layer Effects by : Joe D. Hoffman
Download or read book Thrust Nozzle Optimization for Non-Equilibrium, Chemically Reacting Flows Including Boundary Layer Effects written by Joe D. Hoffman and published by . This book was released on 1969 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: An optimization analysis and a method for the application of the results are presented for the design of axisymmetric or two-dimensional optimum thrust nozzles for non-equilibrium chemically reacting flows including boundary layer effects. The analysis is based on the usual assumptions applicable to non-equilibrium, chemically reacting flows, and on the assumption that the boundary layer is thin. The problem is formulated to maximize the pressure thrust integral along the supersonic wall contour for a general isoperimetric design constraint. The results of the optimization analysis are a set of hyperbolic partial differential equations for determining the Lagrange multipliers of the optimization problem in the region of interest, and a set of algebraic equations for determining the initial and boundary conditions for these multipliers on the boundaries of the region. Two special cases of the general results for non-equilibrium, chemically reacting flows are presented. These are: (1) flow of a simple dissociating gas, and (2) equilibrium or frozen flow of a general gas mixture. Nozzle design schemes for these two special cases are derived by appropriate reduction of the results for the general case. Numerical schemes for these special cases are discussed. (Author).
Book Synopsis A Parametric Study of Boundary Layer Effects on Maximum Thrust Nozzle Contours by : Joe D. Hoffman
Download or read book A Parametric Study of Boundary Layer Effects on Maximum Thrust Nozzle Contours written by Joe D. Hoffman and published by . This book was released on 1969 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: An optimization analysis employing the calculus of variations and a numerical relaxation scheme for applying the results are presented for the design of optimum, axisymmetric thrust nozzle contours including boundary layer effects. The method is illustrated by comparison with a known solution without boundary layer effects. A parametric study of boundary layer effects for a range of parameters typical of scramjet operation is presented. (Author).
Book Synopsis Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles, Including Boundary Layer, Turbulence, and Real Gas Effects by : Ralph C. Tolle
Download or read book Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles, Including Boundary Layer, Turbulence, and Real Gas Effects written by Ralph C. Tolle and published by . This book was released on 1996 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781792786242 Total Pages :32 pages Book Rating :4.7/5 (862 download)
Book Synopsis Investigation of Low-Reynolds-Number Rocket Nozzle Design Using Pns-Based Optimization Procedure by : National Aeronautics and Space Adm Nasa
Download or read book Investigation of Low-Reynolds-Number Rocket Nozzle Design Using Pns-Based Optimization Procedure written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-12-31 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: An optimization approach to rocket nozzle design, based on computational fluid dynamics (CFD) methodology, is investigated for low-Reynolds-number cases. This study is undertaken to determine the benefits of this approach over those of classical design processes such as Rao's method. A CFD-based optimization procedure, using the parabolized Navier-Stokes (PNS) equations, is used to design conical and contoured axisymmetric nozzles. The advantage of this procedure is that it accounts for viscosity during the design process; other processes make an approximated boundary-layer correction after an inviscid design is created. Results showed significant improvement in the nozzle thrust coefficient over that of the baseline case; however, the unusual nozzle design necessitates further investigation of the accuracy of the PNS equations for modeling expanding flows with thick laminar boundary layers. Hussaini, M. Moin and Korte, John J. Langley Research Center NASA-TM-110295, NAS 1.15:110295 RTOP 522-31-31-02...
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 818 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Ejectors for Efficient Refrigeration by : Giuseppe Grazzini
Download or read book Ejectors for Efficient Refrigeration written by Giuseppe Grazzini and published by Springer. This book was released on 2018-03-21 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt: Encompassing both practical applications and recent research developments, this book takes the reader from fundamental physics, through cutting-edge new designs of ejectors for refrigeration. The authors’ unique vision marries successful design, system optimization, and operation experience with insights on the application of cutting-edge Computational Fluid Dynamics (CFD) models. This robust treatment leads the way forward in developing improved ejector technologies. The book covers ejectors used for heat powered refrigeration and for expansion work recovery in compression refrigerators, with special emphasis on two-phase flows of “natural” fluids within the ejector, i.e. steam and carbon dioxide. It features worked examples, detailed research results, and analysis tools.
Book Synopsis Maximum Thrust Nozzles for Rotational Or Nonequilibrium Simple Dissociating Gas Flows Including Boundary Layer Effects by : M. Peter Scofield
Download or read book Maximum Thrust Nozzles for Rotational Or Nonequilibrium Simple Dissociating Gas Flows Including Boundary Layer Effects written by M. Peter Scofield and published by . This book was released on 1969 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Maximum Thrust Nozzles for Rotational Or Nonequilibrium Simple Dissociating Gas Flows Including Boundary Layer Effects by : M. Peter Scofield
Download or read book Maximum Thrust Nozzles for Rotational Or Nonequilibrium Simple Dissociating Gas Flows Including Boundary Layer Effects written by M. Peter Scofield and published by . This book was released on 1969 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: A formulation, numerical solution technique and computer program implementing the technique are presented for the design of maximum thrust nozzles for rotational or nonequilibrium simple dissociating gas flows including boundary layer effects. The formulation is based on the usual assumptions applicable to rotational and nonequilibrium simple dissociating gas flows and on the assumption that the boundary layer is thin. The thrust is written as the integral of the stress tensor acting along the supersonic nozzle wall on which a general isoperimetric design constraint is also applied. The thrust expression is maximized by application of the calculus of variations. The resulting set of design equations are hyperbolic partial differential equations valid in the region of interest and algebraic equations specifying the boundary conditions for the Lagrange multipliers of the extremal problem. The numerical solution technique presented is based on a simplified relaxation technique which does not require numerical differentiation. The results of a brief study to determine the magnitude of the performance increases that can be expected by considering more accurate flow chemistry models are also presented. (Author).
Book Synopsis Maximum Thrust Nozzles for Rotational Or Nonequilibrium Simple Dissociating Gas Flows Including Boundary Layer Effects by : M. Peter Scofield
Download or read book Maximum Thrust Nozzles for Rotational Or Nonequilibrium Simple Dissociating Gas Flows Including Boundary Layer Effects written by M. Peter Scofield and published by . This book was released on 1969 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt: A formulation, numerical solution technique and computer program implementing the technique are presented for the design of maximum thrust nozzles for rotational or nonequilibrium simple dissociating gas flows including boundary layer effects. The formulation is based on the usual assumptions applicable to rotational and nonequilibrium simple dissociating gas flows and on the assumption that the boundary layer is thin. The thrust is written as the integral of the stress tensor acting along the supersonic nozzle wall on which a general isoperimetric design constraint is also applied. The thrust expression is maximized by application of the calculus of variations. The resulting set of design equations are hyperbolic partial differential equations valid in the region of interest and algebraic equations specifying the boundary conditions for the Lagrange multipliers of the extremal problem. The numerical solution technique presented is based on a simplified relaxation technique which does not require numerical differentiation. It is felt that this new solution technique will encourage the use of the general design formulation. The results of a brief study to determine the magnitude of the performance increases that can be expected by considering more accurate flow chemistry models are also presented. The results indicate that significant improvements may be possible. (Author).
Book Synopsis Optimization of Supersonic Rocket Nozzles with Viscous Flow by : Hae Ung Hwang
Download or read book Optimization of Supersonic Rocket Nozzles with Viscous Flow written by Hae Ung Hwang and published by . This book was released on 1970 with total page 280 pages. Available in PDF, EPUB and Kindle. Book excerpt: The determination of the optimum shape of a supersonic (rocket motor) nozzle, under the constraint of a given surface area, while taking into account the effects of viscous action and heat conduction, is the objective of the investigation. In the case of a nozzle (low density or low Reynolds number) where the effects of viscous action and heat conduction extend over the entire flow field, the optimization problem for a conical nozzle was solved on the basis of postulated similar solutions. For more general application, where a thin boundary layer can be postulated, the optimization of a contoured (axisymmetric) nozzle was undertaken by adopting one of two approaches, namely one involving a physical boundary layer region and another involving the displacement thickness of the boundary layer. In both cases, it is the objective to consider the inviscid and the viscous regions governed by appropriate flow equations simultaneously in determining the necessary conditions. This method of subjecting two simply-connected regions simultaneously to optimization is developed for the first time and can be extended in many directions. (Author).
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1971 with total page 776 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Design of Maximum Thrust Plug Nozzles with Variable Inlet Geometry. Volume II. Computer Program Manual by : Gearold R. Johnson
Download or read book Design of Maximum Thrust Plug Nozzles with Variable Inlet Geometry. Volume II. Computer Program Manual written by Gearold R. Johnson and published by . This book was released on 1971 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of designing two-dimensional or axisymmetric plug nozzles with variable inlet geometry which produce the maximum axial thrust when an engineering constraint is imposed on the plug contour, for example, fixed length, has been formulated and numerically solved. The formulation was written to consider a gas mixture whose composition is either fixed or in chemical equilibrium. The effects of the boundary layer thickness and the wall shear stress are included in the problem formulation. The optimization analysis and the results from selected parametric studies are presented in Volume I of this report. This volume, Volume II, contains a description of the computer program, a discussion of the input parameters, and the results of six sample cases. (Author).
Book Synopsis Effects of Convoluted Divergent Flap Contouring on the Performance of a Fixed-Geometry Nonaxisymmetric Exhaust Nozzle by : Scott C. Asbury
Download or read book Effects of Convoluted Divergent Flap Contouring on the Performance of a Fixed-Geometry Nonaxisymmetric Exhaust Nozzle written by Scott C. Asbury and published by . This book was released on 1999 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Approximate Theoretical Method for Modeling the Static Thrust Performance of Non-axisymmetric Two-dimensional Convergent-divergent Nozzles by :
Download or read book An Approximate Theoretical Method for Modeling the Static Thrust Performance of Non-axisymmetric Two-dimensional Convergent-divergent Nozzles written by and published by . This book was released on 1995 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Thrust Coefficients of Low-thrust Nozzles by : Ernie W. Spisz
Download or read book Thrust Coefficients of Low-thrust Nozzles written by Ernie W. Spisz and published by . This book was released on 1965 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The performance losses associated with small nozzles operating at low propellant flow rates were investigated experimentally with a resistance-heated hydrogen thrustor. Data were obtained for seven different nozzles covering the range of nozzle area ratio from 25 to 150, hydrogen propellant flow rates of 0.5x10 to the -4, 1.0x10 to the -4, and 2.5x10 to the -4 pound per second, and propellant temperatures from 530 to 4000 R. The nozzle losses, as determined by the difference between the one-dimensional isentropic thrust coefficient and the measured thrust coefficient, were correlated in terms of the throat Reynolds number and nozzle area ratio. At low throat Reynolds number, the nozzle losses were sufficiently large to result in measured thrust coefficients less than the values calculated for isentropic flow through a choked orifice. Results show that large area ratios are not required for achieving maximum thrust for nozzles with low throat Reynolds number (
Book Synopsis Experimental Thrust Performance of a High-area-ratio Rocket Nozzle by : Albert J. Pavli
Download or read book Experimental Thrust Performance of a High-area-ratio Rocket Nozzle written by Albert J. Pavli and published by . This book was released on 1987 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
