Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Propulsion Nozzle Studies Volume Ii Design Of Maximum Thrust Nozzle Base Boattail Contours
Download Propulsion Nozzle Studies Volume Ii Design Of Maximum Thrust Nozzle Base Boattail Contours full books in PDF, epub, and Kindle. Read online Propulsion Nozzle Studies Volume Ii Design Of Maximum Thrust Nozzle Base Boattail Contours ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Propulsion Nozzle Studies. Volume II. Design of Maximum Thrust Nozzle-Base-Boattail Contours by : Jeffrey G. Allman
Download or read book Propulsion Nozzle Studies. Volume II. Design of Maximum Thrust Nozzle-Base-Boattail Contours written by Jeffrey G. Allman and published by . This book was released on 1977 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt: A production-type computer program was developed for the design of maximum thrust axisymmetric nozzle-base-boattail contours. The flow field analysis is based on the governing equations for the rotational flow of a frozen or equilibrium gas mixture. The contour optimization is based on the direct optimization of a nonlinear function of several (three or less) geometric variables. The nozzle and boattail contours are modeled as a second-order polynomial and a cone, respectively. For fixed initial contours and nozzle and boattail lengths, the second-order polynomial nozzle contour is uniquely specified by the nozzle throat attachment angle and the nozzle exit lip radius, and the conical boattail is uniquely specified by the boattail exit lip radius. These three independent parameters are varied to determine the unique nozzle-base-boattail configuration that yields maximum thrust. Three methods are included in the program to determine the maximum thrust contour. Each method requires an initial estimate of the geometry that produces maximum thrust. The three methods were also applied to the design of nozzle-base-boattail configurations. The three-dimensional optimizations were found to be practical for finding the maximum thrust attainable for a nozzle-base-boattail assembly. Each of the three methods converged efficiently to the maximum thrust nozzle-base-boattail contour.
Download or read book Propulsion Nozzle Studies written by and published by . This book was released on 1976 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1977 with total page 276 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Design of Maximum Thrust Nozzles for Gas-Particle Flows. Volume II. Computer Program Manual by : Arnold A. Elsbernd
Download or read book Design of Maximum Thrust Nozzles for Gas-Particle Flows. Volume II. Computer Program Manual written by Arnold A. Elsbernd and published by . This book was released on 1971 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program description, description of input parameters and four sample cases for the design program used to obtain maximum thrust nozzle contours for gas-particle flows are presented. The optimization analysis and the results of certain parametric studies were presented in Volume 1 of this report. Volume 2 contains a description of the program organization and overlay structure, a description of each subroutine, a description of the input parameters and their default values, and four sample cases to illustrate the use of the design program. (Author).
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 Design of Maximum Thrust Nozzles with Nonequilibrium, Chemically Reacting Flow. Volume II. Computer Program Manual by : Allan A. Taylor
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).
Book Synopsis Design of Maximum Thrust Nozzles for Gas-Particle Flows. Volume 1. Theoretical Development and Results by :
Download or read book Design of Maximum Thrust Nozzles for Gas-Particle Flows. Volume 1. Theoretical Development and Results written by and published by . This book was released on 1971 with total page 101 pages. Available in PDF, EPUB and Kindle. Book excerpt: An optimization analysis is presented for nozzles with gas-particle flows. The problem is formulated to maximize the axial thrust produced along the nozzle contour for a general isoperimetric constraint such as constant nozzle length or constant nozzle surface area. The effects of the ambient pressure are included in the thrust expression to be maximized. The characteristic and compatibility equations are developed and numerical techniques are presented for use in conjunction with the characteristic and compatibility equations. A solution procedure is presented which determines whether or not a given nozzle contour is an optimal solution and a relaxation technique is presented which adjusts the nozzle contour toward the optimal solution. Selected parametric studies are presented. These studies illustrate the effects of changing mesh size, particle size, particle mass flow rate, inlet angle, drag coefficients, heat transfer coefficients, throat radius of curvature, and the scale on the thrust performance and the nozzle geometry of the optimal, fixed length nozzle.
Book Synopsis Government Reports Announcements & Index by :
Download or read book Government Reports Announcements & Index written by and published by . This book was released on 1995 with total page 1166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three-Dimensional Nozzle Design for Maximum Thrust. Volume II. Computer Program Manual by : Lynn E. Snyder
Download or read book Three-Dimensional Nozzle Design for Maximum Thrust. Volume II. Computer Program Manual written by Lynn E. Snyder and published by . This book was released on 1971 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of designing three-dimensional (nonaxisymmetric) supersonic nozzles which produce the maximum axial thrust for a prescribed upstream flow field, mass flow rate, exit lip shape and position, and ambient pressure has been formulated and numerically solved. The formulation was written to consider a three-dimensional, supersonic, isoenergetic, homentropic flow of a perfect gas. This volume contains a description of the computer program organization and overlay structure, a description of each main program and each subroutine, a description of the input parameters, and the input listing and selected output for a sample case to illustrate the use of the design programs. (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 Design of Maximum Thrust Nozzles with Nonequilibrium, Chemically Reacting Flow. Volume I. Theoretical Development and Results by : Allan A. Taylor
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).
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 1977 with total page 866 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental and Analytical Determination of Integrated Airframe Nozzle Performance by : Edsel R. Glasgow
Download or read book Experimental and Analytical Determination of Integrated Airframe Nozzle Performance written by Edsel R. Glasgow and published by . This book was released on 1972 with total page 714 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental and analytical investigation of the installed thrust and drag of various isolated nozzle and twin-nozzle/aftbody configurations indicated that empirical correlations provide the best means of predicting aft- end performance, especially for the early stages of the aircraft design. Both subsonic and transonic isolated nozzle drag data were correlated using IMS (integral mean slope) as the geometric parameter. A correlation of twin-nozzle/aftbody drag data at subsonic and transonic speeds was developed by combining Spreiter's transonic similarity parameters with the IMS of the equivalent body of revolution. A correlation of inviscid MOC pressure drag, achieved through use of IMS combined with similarity parameters obtained from linearized supersonic flow theory, provided an accurate and rapid means of estimating drag for arbitrary axisymmetric boattail contours at supersonic speeds. Twin-nozzle/aftbody drag data at supersonic speeds was correlated with the equivalent body drag obtained from the axisymmetric MOC correlation. Improved thrust and drag performance was obtained by modifying the aft-end design of five selected aircraft configurations. The rationale for these modifications was derived from design guidelines and criteria developed during the program. Improvements in mission radius for a fixed takeoff gross weight aircraft were obtained, in general, by utilizing convergent-divergent nozzles, a horizontal wedge interfairing with the trailing edge terminating at the exit plane of the nozzles, a single vertical stabilizer, and a narrow lateral nozzle spacing.
Book Synopsis Experimental and Analytical Determination of Integrated Airframe Nozzle Performance by : Edsel R. Glasgow
Download or read book Experimental and Analytical Determination of Integrated Airframe Nozzle Performance written by Edsel R. Glasgow and published by . This book was released on 1972 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer program has been developed for predicting twin-nozzle/aftbody drag and internal nozzle performance for fighter type aircraft having twin buried engines and dual nozzles. The program is capable of generating the installed thrust-minus-drag data required for conducting mission analysis studies of aircraft of this type. The configuration variables which can be analyzed include (1) nozzle type (convergent flap and iris, convergent-divergent with and without secondary flow, and shrouded and unshrouded plug), (2) nozzle lateral spacing, (3) interfairing type (horizontal and vertical wedge), (4) interfairing length, and (5) vertical stabilizer type (single and twin). The performance prediction methods incorporated in the program are based almost entirely on empirical correlations. Specifically, correlations used in conjunction with one-dimensional flow relationships are employed for the prediction of the nozzle thrust and discharge coefficients, and correlations of the test data obtained during the contracted effort are employed for prediction of the aft-end drag. The prediction methods account for the effects of nozzle pressure ratio and flow separation on both internal and external nozzle surfaces. This manual describes the operation of the computer program in terms of program input requirements, performance prediction methods, and output format and includes a presentation of sample input/output cases and a complete computer listing of the program. The program has been developed for use on the CDC 6600 computer.
Book Synopsis Three-Dimensional Nozzle Design for Maximum Thrust. Volume I. Theoretical Development and Results by : Lynn E. Snyder
Download or read book Three-Dimensional Nozzle Design for Maximum Thrust. Volume I. Theoretical Development and Results written by Lynn E. Snyder and published by . This book was released on 1970 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of designing three-dimensional (nonaxisymmetric) supersonic nozzles which produce the maximum axial thrust for a prescribed upstream flow field, mass flow rate, exit lip shape and position, and ambient pressure was formulated and numerically solved. The formulation was written to consider a three-dimensional, supersonic, isoenergetic, homentropic flow of a perfect gas. The axial thrust and mass flow rate were written as integrals over a control surface which was constrained to pass through the exit lip of the nozzle. The functional to be maximized was formed by summing the integral equation for the axial thrust and the integral equation for the mass flow rate times a Lagrange multiplier. The fixed length and fixed ambient pressure constraints were imposed by substitution into the variational problem. The numerical solution technique was programmed for the CDC 6500 computer. The results confirm that the three-dimensional optimal nozzles designed using this technique are significantly better than three-dimensional nozzles that have identical initial conditions and have comparable overall dimensions. Furthermore, the results show that two-dimensional or axisymmetric methods are not adequate for designing three-dimensional optimum nozzles. (Author).
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1993 with total page 936 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Design of Maximum Thrust Plug Nozzles for Fixed Inlet Geometry by : H. Doyle Thompson
Download or read book Design of Maximum Thrust Plug Nozzles for Fixed Inlet Geometry written by H. Doyle Thompson and published by . This book was released on 1970 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt: The calculus of variations is used to obtain and design equations for the contour of maximum thrust plug nozzles with a fixed inlet geometry and a specified geometric constraint. The optimum values of the injection angle at the throat and the cowl lip radius are determined by a parametric study. The analysis is carried out for irrotational flow and includes boundary layer effects. A method is presented to determine if a given contour is an optimum, and a relaxation technique is used to obtain a solution to the resulting design equations. Numerical examples are presented for a fixed plug length and mass flow rate. (Author).
