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Author : Keith S. McDaniel
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ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Three-dimensional Simulation of Thermal Choking in a Model Scramjet Combustor written by Keith S. McDaniel and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Keith S. McDaniel
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Simulation of Thermal Choking in a Model Scramjet Combustor written by Keith S. McDaniel and published by . This book was released on 1999 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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ISBN 13 :
Total Pages : 9 pages
Book Rating : 4.:/5 (742 download)
Download or read book Parallel Modeling of Three-Dimensional Scramjet Combustor and Comparisons with Experiment's Results written by and published by . This book was released on 2002 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this paper a parallel simulation of an experimental dual-mode scramjet combustor configuration is presented. Turbulence is modeled with the kappa-epsilon two-equation turbulence model and a 7-species 8-equation kinetics model is used to model hydrogen/air combustion. The conservation from of the Navier-Stokes equations with finite-rate chemistry reactions is solved using a diagonal implicit finite-volume method. Using about 3,12O,000 grid points the three-dimension flow-fields with equivalence ratio phi=0.0 and 0.35 have been respectively simulated on the parallel computer system obtaining more detailed flow properties than the experiment's results. Wall pressure comparisons between CFD and experiment show fair agreement. For phi=0.35 the fuel-penetrating height of the seven injectors are different because of the effects of the boundary layer and the shock wave in the combustor. According to numerical results, if adjusting the locations of the injectors the combustion efficiency could be improved.
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ISBN 13 :
Total Pages : 14 pages
Book Rating : 4.:/5 (317 download)
Download or read book Three Dimensional Numerical Simulation of Rocket-Based Combined-Cycle Engine Response During Mode Transition Events written by and published by . This book was released on 2003 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Commemorazione funebre del deputato Sella written by and published by . This book was released on 1884 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (317 download)
Download or read book Three Dimensional CFD Analysis of the GTX Combustor written by and published by . This book was released on 2002 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Three Dimensional Simulation of Time-Dependent Scramjet Isolator /Combustor Flowfields Implemented on Parallel Architectures written by and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The development of a parallel Navier-Stokes solver for computing time-dependent, three-dimensional reacting flowfields within scramjet (supersonic combusting ramjet)engines is presented in this work. The algorithm combines low-diffusion upwinding methods, timeaccurate implicit integration techniques, and domain decomposition strategies to yield an effective approach for large-scale simulations. The algorithm is mapped to a distributed memoryIBM SP-2 architecture and a shared memory Compaq ES-40 architecture using the MPI-1 message-passingstandard. Two and three-dimensional simulations of time-dependent hydrogen fuel injection into a modelscramjet isolator / combustor configuration at two equivalence ratios are performed. Thesesimulations are used to gain knowledge of engine operability, inlet performance, isolatorperformance, fuel air mixing, flame holding, mode transition, and engine unstart. Results for an injection at a ratio of 0.29 show qualitative agreement withexperiment for the two-dimensional case, but revealed a slow progression towardengine unstart for the three-dimensional case. Injection at an equivalence ratio of 0.61resulted in engine unstart for both two-dimensional and three-dimensional cases. Engine unstart for the three-dimensional case occurs as a response to the formation and growthof large pockets of reversed flow along the combustor side wall. These structuresdevelop at an incipient pressure above 154 kPa and result in significant blockage of the core flow, additional compression, and chemical reaction within the boundary layer. All of these factors promotea much more rapid unstart as compared with the two-dimensional case.
Download or read book Numerical Simulation of Scramjet Combustion in a Shock Tunnel written by and published by . This book was released on 2004 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Three-dimensional computational simulations of reactive flowfields within a hydrogen-fueled scramjet-like geometry experimentally tested in a free piston shock tunnel are presented. The experimental configuration (Odam and Paull, AIAA Paper 2003-5244) involves injection of hydrogen fuel into the scramjet inlet, followed by mixing, shock-induced ignition, and combustion. The predictions for both fuel-off and fuel-on conditions were observed to be sensitive to the choice of the wall temperature boundary conditions. The best comparison with experimental data were achieved through the implementation of an approach that involves a simplified conjugate heat transfer model that couples the heat conduction through the wall with the heat conduction of the fluid within the boundary layer. This approach is able to predict thermal loads on the walls of the scramjet model due to shock wave interactions and due to heat release. As such, it is able to more accurately represent the physical temperature response of the engine model. Also shown to produce very good agreement with the statistically-steady experimental data was the isothermal ghost-cell boundary condition, which is based on a simplification of the time-dependent conjugate heat transfer boundary condition. This simplified boundary condition assumes a linear temperature distribution within the wall based on the effective depth that an applied heat load would penetrate, thus, it also allows the actual wall temperature to vary in response to the applied heat load. Results for fuel-off simulations showed that the solution generated by a steady-state simulation implementing the isothermal ghost-cell wall boundary condition was very comparable with the statistically-steady solution obtained from a fully transient simulation with coupled heat conduction within the walls. When integrated in a fully time-accurate manner, the fuel-on simulations showed a striking sensitivity to the modeled rate of air ingestion into the engine. F.
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ISBN 13 :
Total Pages : 598 pages
Book Rating : 4.0/5 ( download)
Download or read book 43rd AIAA Aerospace Sciences Meeting & Exhibit written by and published by . This book was released on 2005 with total page 598 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721145089
Total Pages : 114 pages
Book Rating : 4.1/5 (45 download)
Download or read book Numerical Investigation of Dual-Mode Scramjet Combustor with Large Upstream Interaction written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-20 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt: Dual-mode scramjet combustor configuration with significant upstream interaction is investigated numerically, The possibility of scaling the domain to accelerate the convergence and reduce the computational time is explored. The supersonic combustor configuration was selected to provide an understanding of key features of upstream interaction and to identify physical and numerical issues relating to modeling of dual-mode configurations. The numerical analysis was performed with vitiated air at freestream Math number of 2.5 using hydrogen as the sonic injectant. Results are presented for two-dimensional models and a three-dimensional jet-to-jet symmetric geometry. Comparisons are made with experimental results. Two-dimensional and three-dimensional results show substantial oblique shock train reaching upstream of the fuel injectors. Flow characteristics slow numerical convergence, while the upstream interaction slowly increases with further iterations. As the flow field develops, the symmetric assumption breaks down. A large separation zone develops and extends further upstream of the step. This asymmetric flow structure is not seen in the experimental data. Results obtained using a sub-scale domain (both two-dimensional and three-dimensional) qualitatively recover the flow physics obtained from full-scale simulations. All results show that numerical modeling using a scaled geometry provides good agreement with full-scale numerical results and experimental results for this configuration. This study supports the argument that numerical scaling is useful in simulating dual-mode scramjet combustor flowfields and could provide an excellent convergence acceleration technique for dual-mode simulations. Mohieldin, T. O. and Tiwari, S. N. and Reubush, David E. (Technical Monitor) Langley Research Center NAG1-2266
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ISBN 13 :
Total Pages : 778 pages
Book Rating : 4.0/5 ( download)
Download or read book 41st AIAA Aerospace Sciences Meeting & Exhibit written by and published by . This book was released on 2003 with total page 778 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Michael M. Resch
Publisher : Springer Science & Business Media
ISBN 13 : 3642222447
Total Pages : 186 pages
Book Rating : 4.6/5 (422 download)
Download or read book High Performance Computing on Vector Systems 2011 written by Michael M. Resch and published by Springer Science & Business Media. This book was released on 2011-12-02 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book presents the state of the art in high performance computing and simulation on modern supercomputer architectures. It covers trends in hardware and software development in general and specifically the future of vector-based systems and heterogeneous architectures. The application contributions cover computational fluid dynamics, material science, medical applications and climate research. Innovative fields like coupled multi-physics or multi-scale simulations are presented. All papers were chosen from presentations given at the 13th Teraflop Workshop held in October 2010 at Tohoku University, Japan.
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ISBN 13 :
Total Pages : 658 pages
Book Rating : 4.0/5 ( download)
Download or read book 39th AIAA Aerospace Sciences Meeting and Exhibit written by and published by . This book was released on 2001 with total page 658 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Long Vu
Publisher :
ISBN 13 :
Total Pages : 87 pages
Book Rating : 4.:/5 (132 download)
Download or read book Quasi-one-dimensional Scramjet Combustor Flow Solver Using the Numerical Propulsion System Simulation written by Long Vu and published by . This book was released on 2019 with total page 87 pages. Available in PDF, EPUB and Kindle. Book excerpt: The flow field inside a scramjet engine combustor involves complex phenomena such as fuel-air mixing, combustion chemistry, and flow separation. In order to determine the properties of the flow along the length of the combustor, mass, momentum and energy balance equations are solved simultaneously using a numerical method. While a full three dimensional computational simulation gives detailed results with high order of accuracy, it demands a great amount of time and computational resource. A low order analysis produces a fast overall picture of the combustor operation which in turn provides valuable information suitable for the preliminary design process. This research work aims to describe the analysis process of the scramjet combustor in which a quasi-one-dimensional, multi-species, reacting real gas model of the flow is developed to address the limitations in previous researches. The Numerical Propulsion System Simulation (NPSS), into which the NASA Chemical Equilibrium with Applications (CEA) code is integrated, is utilized as the platform to perform the analysis. The analytical model is validated by comparison with experimental data from previous researches. The results obtained by this method are expected to shed some light on the advantages of using detailed chemistry with lower order analysis to calculate scramjet engine performance.
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ISBN 13 :
Total Pages : 566 pages
Book Rating : 4.0/5 ( download)
Download or read book AIAA Aerospace Sciences Meeting and Exhibit, 42nd written by and published by . This book was released on 2004 with total page 566 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Houshang B. Ebrahimi
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Two and Three Dimensional Parabolized Navier-Stokes Code for Scramjet Combustor, Nozzle and Film Cooling Analysis written by Houshang B. Ebrahimi and published by . This book was released on 1992 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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ISBN 13 :
Total Pages : 1032 pages
Book Rating : 4.F/5 ( download)
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 1032 pages. Available in PDF, EPUB and Kindle. Book excerpt:
