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Computational Methods To Optimize Supersonic Nozzles
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Book Synopsis Computational Methods to Optimize Supersonic Nozzles by : Igor Gaissinski
Download or read book Computational Methods to Optimize Supersonic Nozzles written by Igor Gaissinski and published by LAP Lambert Academic Publishing. This book was released on 2013 with total page 400 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book is devoted to calculation methods of a converging-diverging nozzle used in propulsion and the high velocity flow. The algorithms and programs given in the book are intended to help engineers and students to design and calculate the nozzle parameters to provide optimal parameters for compressible supersonic flows. The present monograph is a tutorial (handbook) to calculate and determine the optimal parameters for converging-diverging nozzles provided supersonic flow. The main program consists from three main parts: programs for calculation the profile of the Contraction zone, EOD code for the flow in the Contraction zone, the program Rott-Crabtree for calculation the pressure gradient Pohlhausen parameter, the program for the aerodynamic design of axisymmetric and two-dimensional nozzles for supersonic and hypersonic wind tunnels, programs for solving laminar, transitional, or turbulent compressible boundary layer equations for two-dimensional and axisymmetric flow, and the program to obtain hypersonic boundary layer stability. The book is designed to be an instrument for students and scientists interested in study supersonic flow and high-temperature gas dynamics.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722272609 Total Pages :26 pages Book Rating :4.2/5 (726 download)
Book Synopsis High Speed Nozzles Task by : National Aeronautics and Space Administration (NASA)
Download or read book High Speed Nozzles Task written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-05 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Supersonic cruise exhaust nozzles for advanced applications are optimized for a high nozzle pressure ratio (NPR) at design supersonic cruise Mach number and altitude. The performance of these nozzles with large expansion ratios are severely degraded for operations at subsonic speeds near sea level for NPR significantly less than the design values. The prediction of over-expanded 2DCD nozzles performance is critical to evaluating the internal losses and to the optimization of the integrated vehicle and propulsion system performance. The reported research work was aimed at validating and assessing existing computational methods and turbulence models for predicting the flow characteristics and nozzle performance at over-expanded conditions. Flow simulations in 2DCD nozzles were performed using five different turbulence models. The results are compared with the experimental data for the wall pressure distribution and thrust and flow coefficients at over-expanded static conditions. Hamed, Awatef Unspecified Center OAI-120520...
Book Synopsis Modern Problems in Computational Aerohydrodynamics by : DorodniCyn/Chus
Download or read book Modern Problems in Computational Aerohydrodynamics written by DorodniCyn/Chus and published by CRC Press. This book was released on 1991-11-19 with total page 410 pages. Available in PDF, EPUB and Kindle. Book excerpt: :This book emphasizes the numerical methods of solving boundary problems for nonlinear equations of aerohydrodynamics, especially partial differential and integro-differential equations. Topics discussed include an analysis of transonic gas flows and three-dimensional supersonic flows, the simulation of viscous fluid flows, perturbation development in a boundary layer, and approaches to constructing adaptive grids. The book will appeal to professional aeronautical engineers, applied physicists, applied mathematicians, and geophysicists. @
Book Synopsis A Computational Environment for Exhaust Nozzle Design by : Andrew Gelsey
Download or read book A Computational Environment for Exhaust Nozzle Design written by Andrew Gelsey and published by . This book was released on 1995 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: "The Nozzle Design Associate (NDA) is a computational environment for the design of jet engine exhaust nozzles for supersonic aircraft. NDA may be used either to design new aircraft or to design new nozzles that adapt existing aircraft so they may be reutilized for new missions. NDA was developed in a collaboration between computer scientists at Rutgers University and exhaust nozzle designers at General Electric Aircraft Engines and General Electric Corporate Research and Development. The NDA project has two principle goals: to provide a useful engineering tool for exhaust nozzle design, and to explore fundamental research issues that arise in the application of automated design optimization methods to realistic engineering problems."
Book Synopsis Pulsed Injection Flow Control for Throttling in Supersonic Nozzles - A Computational Fluid Dynamics Design Study (Preprint). by :
Download or read book Pulsed Injection Flow Control for Throttling in Supersonic Nozzles - A Computational Fluid Dynamics Design Study (Preprint). written by and published by . This book was released on 2007 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: A vehicle propelled by an engine with a variable geometry nozzle allows the nozzle expansion ratio to vary with altitude and flight condition, thereby optimizing engine performance. Active flow control offers a method of providing the functionality of a variable throat area system without requiring variable geometry. Throttling the mass flow rate through the nozzle throat controls the effective throat area, subsequently controlling the effective expansion ratio of the overall nozzle. This paper presents findings from the Pulsed Injection for Rocket Flow Control Technology (PIRFCT) program, which evaluated potential gains in the overall performance of a rocket using active flow control to optimize nozzle expansion ratio for an Earth to orbit mission. Lockheed Martin Aeronautics Company utilized Computational Fluid Dynamics (CFD) to simulate the rocket nozzle with active flow control. Simulations were performed with steady and pulsed flow control jets which were oriented near the geometric throat and inclined upstream against the primary flow. A low stagnation pressure, steady, tertiary injection stream when combined with a steady, high momentum secondary injector was witnessed to increase throttling performance beyond that of a secondary injector alone. Nozzle discharge coefficient was largely unaffected by changes in pulsation frequency or pulsation duty cycle. Pulsed injection approached, but did not exceed, the throttling performance of a time invariant injector when compared on a equivalent mass flux, momentum flux, and energy flux basis. Simulations incorporating a single injector and large area modulations predicted a 50% area reduction when injecting approximately 18% baseline reference mass flow at Mach 2 conditions. However, the PIRFCT program concluded that secondary injection at the nozzle throat is not a good candidate for this type of throttling/altitude compensation technology for an Earth to orbit mission.
Book Synopsis Flow Analysis and Design Optimization Methods for Nozzle Afterbody of a Hypersonic Vehicle by : Oktay Baysal
Download or read book Flow Analysis and Design Optimization Methods for Nozzle Afterbody of a Hypersonic Vehicle written by Oktay Baysal and published by . This book was released on 1992 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Applications of Computational Methods in Manufacturing and Product Design by : B. B. V. L. Deepak
Download or read book Applications of Computational Methods in Manufacturing and Product Design written by B. B. V. L. Deepak and published by Springer Nature. This book was released on 2022-05-04 with total page 663 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book presents the select proceedings of the conference of Innovative Product Design and Intelligent Manufacturing System (IPDIMS 2020), held at the National Institute of Technology, Rourkela, India. The book addresses latest methods and advanced tools from different areas of design and manufacturing technology. The main topics covered include computational methods for robotics, mechatronics and human-computer interaction; computer-aided design, manufacturing and engineering; aesthetics, ergonomics and UX/UI design; smart manufacturing and expert systems. The contents of this book will be useful for researchers as well as professionals working in the areas of industrial design, mechatronics, robotics, and automation.
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 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computer Program for Design of Two-dimensional Sharp-edged-throat Supersonic Nozzle with Boundary Layer Correction by : Louis J. Goldman
Download or read book Computer Program for Design of Two-dimensional Sharp-edged-throat Supersonic Nozzle with Boundary Layer Correction written by Louis J. Goldman and published by . This book was released on 1971 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Study of Equilibrium Real-gas Effects in Hypersonic Air Nozzles, Including Charts of Thermodynamic Properties for Equilibrium Air by : Wayne Douglas Erickson
Download or read book A Study of Equilibrium Real-gas Effects in Hypersonic Air Nozzles, Including Charts of Thermodynamic Properties for Equilibrium Air written by Wayne Douglas Erickson and published by . This book was released on 1960 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pulsed Injection Flow Control for Throttling in Supersonic Nozzles - A Computational Fluid Dynamics Based Performance Correlation (Preprint). by :
Download or read book Pulsed Injection Flow Control for Throttling in Supersonic Nozzles - A Computational Fluid Dynamics Based Performance Correlation (Preprint). written by and published by . This book was released on 2007 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: A vehicle propelled by an engine with a variable geometry nozzle allows the nozzle expansion ratio to vary with altitude and flight condition, thereby optimizing vehicle performance. Rockets are examples of vehicles with high nozzle pressure ratios (NPRs), which operate over a large altitude range. Active flow control offers a method of reducing the effective aerodynamic throat of a rocket nozzle in a geometrically fixed structure. Throttling the mass flow rate through the nozzle throat controls the effective throat area, subsequently controlling the effective expansion ratio of the overall nozzle. This paper presents findings from the Pulsed Injection for Rocket Flow Control Technology (PIRFCT) program, which was funded by the Defense Advanced Research Projects Agency (DARPA), and managed by the Air Force Research Laboratory (AFRL). PIRFCT evaluated potential gains in the overall performance of a rocket using active flow control at the throat for throttling. Lockheed Martin Aeronautics Company used Computational Fluid Dynamics (CFD) to simulate a high NPR rocket nozzle with active flow control. Simulations were performed with steady and pulsed flow control jets which were oriented near the throat and directed upstream at a 45-degree angle against the primary flow, and various injection conditions were modeled. All simulations were performed with the perfect gas assumption with the specific heat ratio (gamma) held constant at the value corresponding to the throat temperature. However, during the course of the program, a correlation was developed which predicts the reduction in discharge coefficient as a function of time-averaged mass flux, momentum flux and energy flux. The correlation was very general and was valid for steady and pulsed cases of various conditions.
Book Synopsis Computer Program for Calculating the Flow Field of Supersonic Ejector Nozzles by : Bernhard H. Anderson
Download or read book Computer Program for Calculating the Flow Field of Supersonic Ejector Nozzles written by Bernhard H. Anderson and published by . This book was released on 1974 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1971 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Book Synopsis Computational Study of Supersonic Jets from Swirl-inducing Nozzles by : Sang Y. Han
Download or read book Computational Study of Supersonic Jets from Swirl-inducing Nozzles written by Sang Y. Han and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computer Program Abstracts written by and published by . This book was released on 1974 with total page 814 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :American Institute of Aeronautics and Astronautics. Technical Information Service Publisher : ISBN 13 : Total Pages :226 pages Book Rating :4.3/5 (91 download)
Book Synopsis The Finding Guide to AIAA Meeting Papers by : American Institute of Aeronautics and Astronautics. Technical Information Service
Download or read book The Finding Guide to AIAA Meeting Papers written by American Institute of Aeronautics and Astronautics. Technical Information Service and published by . This book was released on 1994 with total page 226 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Profiling the Supersonic Section of an Axisymmetric Maximum Thrust Nozzle by : A. A. Sergienko
Download or read book Profiling the Supersonic Section of an Axisymmetric Maximum Thrust Nozzle written by A. A. Sergienko and published by . This book was released on 1967 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of the optimum shaping of the supersonic portion of the nozzle is studied within the framework of the variational approach. Such degenerated variational problems are solved by means of the coupled variations at the different ends of the extremum curve which allow the positioning of the extremum curve through two assigned points. The basic relationships and the mathematical formulation of the problem are followed by a study of the extremum equation solution, the condition of transversality of the contour with fixed coordinate points, the presentation of the computational methods, a brief analysis of accuracy, and the presentation of the tabulated results. These show that the solution of the degenerated problem coincides with the solution obtained by means of the classical variational calculus of nondegenerate problems.
