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).
Download or read book Design of Maximum Thrust Nozzles with Nonequilibrium Chemically Reacting Flow Volume I Theoretical Development and Results written by Allan A. Taylor and published by . This book was released on 1971 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis is presented which permits the design of maximum thrust nozzles for nonequilibrium chemically reacting gas flows. The analysis is based upon the governing equations for a general, multi-component reacting gas. The effects of viscosity, multiple phases, body forces and mixing are neglected. All other states of the gas are assumed to be in equilibrium. Design of the nozzle contour is posed subject to a general isoperimetric constraint. The thrust to be maximized is written in terms of an integral of the pressure forces on the nozzle wall. The design constraints and governing equations are incorporated into the integral to be maximized by means of Lagrange multipliers. (Author).
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).
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).
Download or read book A Time dependent Analysis for Quasi one dimensional Nozzle Flows with Vibrational and Chemical Nonequilibrium written by John David Anderson (Jr.) and published by . This book was released on 1969 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new technique is presented for the numerical solution of quasi-one-dimensional, vibrational and chemical nonequilibrium nozzle flows including nonequilibrium conditions both upstream and downstream of the throat. This new technique is a time-dependent analysis which entails the explicite finite-difference solution of the quasi-one-dimensional unsteady flow equations in steps of time, starting with assumed initial distributions throughout the nozzle. The steady-state solution is approached at large values of time. A virtue of the present time-dependent analysis is its simplicity, which prevails from its initial physical formulation to the successful receipt of numerical results. Also, the present solution yields the transient as well as the steady-state nonequilibrium nozzle flows. To exemplify the present analysis, results are given for several cases of vibrational and chemical nonequilibrium expansions through nozzles. (Author).
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:
Download or read book Inviscid and Viscous Hypersonic Nozzle Flow with Finite Rate Chemical Reactions written by E. S. Levinsky and published by . This book was released on 1963 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: Procedures are developed for determining the inviscid core and boundary layer development in diverging nozzles with high enthalpy reservoir conditions in which the gas composition has been displaced from equilibrium by chemical relaxation. A finite difference procedure, based on the method of characteristics, is used for the inviscid flow with finite rate chemical reactions. Laminar boundary layer profiles, based on local similarity, are obtained by integrating the coupled boundary layer and chemical reaction equations outward from the nozzle wall. Free stream boundary conditions on the chemical specie concentrations and the thermodynamic variables are satisfied by iterating o the unknow concentrations and derivatives at the wall. Numerical calculations are presented for the AEDC, VKF low density tunnel and the Convair hypersonic shock tunnel. Effects of chemical reactions in the boundary layer are restricted to the region in which the core flow has not yet frozen and in which the boundary layer is thin. When the boundary layer is thick enough to influence the core expansion, gas phase reactions are frozen. (Author).
Download or read book Design of Maximum Thrust Nozzles with Nonequilibrium Chemically Reacting Flow Volume II Computer Program Manual written by Allan A. Taylor and published by . This book was released on 1971 with total page 89 pages. Available in PDF, EPUB and Kindle. Book excerpt: Volume I of this report contains the theoretical development for design of maximum thrust nozzles with nonequilibrium, chemically reacting flow. The results of selected parametric studies are also presented. This volume contains a discussion of the computer program that was developed to permit the design capability. The organization of the program is presented and general information is given. An abbreviated description of all the subroutines is given. The input data are discussed in some depth, to assist the potential designer. Finally, four sample cases are presented, one in detail to illustrate the various input options. (Author).
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).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 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 1966 with total page 616 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Vibrational Nonequilibrium on the Inviscid Design of an Axisymmetric Nozzle for Hypersonic Flow written by John Benjamin Anders and published by . This book was released on 1975 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1994 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book AIAA 71 41 AIAA 71 65 written by and published by . This book was released on 1971 with total page 466 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by and published by . This book was released on 1987 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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).
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 974 pages. Available in PDF, EPUB and Kindle. Book excerpt:
