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Book Numerical Simulation of Shock Induced Combustion

Download or read book Numerical Simulation of Shock Induced Combustion written by Myles Andrew Sussman and published by . This book was released on 1994 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Numerical Simulation of Shock induced Combustion Around an Axisymmetric Blunt Body

Download or read book Numerical Simulation of Shock induced Combustion Around an Axisymmetric Blunt Body written by Akiko Matsuo and published by . This book was released on 1991 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Numerical Simulation of Hypersonic Shock induced Combustion Ramjet Flowfields

Download or read book Numerical Simulation of Hypersonic Shock induced Combustion Ramjet Flowfields written by Rudolph Dudebout and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Numerical Simulation of Shock Induced Combustion Past Blunt Bodies Using Shock Fitting Technique

Download or read book Numerical Simulation of Shock Induced Combustion Past Blunt Bodies Using Shock Fitting Technique written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-09 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two-dimensional axisymmetric, reacting viscous flow over blunt projectiles is computed to study shock-induced combustion at Mach 5.11 and Mach 6.46 in hydrogen-air mixture. A finite-difference, shock-fitting method is used to solve the complete set of Navier-Stokes and species conservation equations. In this approach, the bow shock represents a boundary of the computational domain and is treated as a discontinuity across which Rankine-Hugoniot conditions are applied. All interior details of the flow such as compression waves, reaction front, and the wall boundary layer are captured automatically in the solution. Since shock-fitting approach reduces the amount of artificial dissipation, all the intricate details of the flow are captured much more clearly than has been possible with the shock-capturing approach. This has allowed an improved understanding of the physics of shock-induced combustion over blunt projectiles and the numerical results can now be explained more readily with one-dimensional wave-interaction model than before. Ahuja, J. K. and Singh, D. J. and Tiwari, S. N. Unspecified Center NAG1-423; NAG1-363...

Book Towards Numerical Simulation of Shock Induced Combustion Using Probability Density Function Approaches

Download or read book Towards Numerical Simulation of Shock Induced Combustion Using Probability Density Function Approaches written by and published by . This book was released on 2002 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: The specific problem to be addressed in this work is the secondary combustion that arises from shock-induced mixing in volumetric explosives. It has been recognized that the effects of combustion due to secondary mixing can greatly alter the expansion of gases and dispersal of high-energy explosive. Furthermore, this enhanced effect may be a tailored feature for the new energetic material systems. One approach for studying this problem is based on the use of Large Eddy Simulation (LES) techniques. In this approach, the large turbulent length scales of motion are simulated directly while the small scales of turbulent motion are explicitly treated using a subgrid scale (SGS) model. The focus of this effort is to develop a SGS model for combustion that is applicable to shock-induced combustion events using probability density function (PDF) approaches. A simplified presumed PDF combustion model is formulated and implemented in the CTH shock physics code. Two classes of problems are studied using this model. The first is an isolated piece of reactive material burning with the surrounding air. The second problem is the dispersal of highly reactive material due to a shock driven explosion event. The results from these studies show the importance of incorporating a secondary combustion modeling capability and the utility of using a PDF-based description to simulate these events.

Book Mit alphabetischem Sachregister zu Band I bis IV

Download or read book Mit alphabetischem Sachregister zu Band I bis IV written by and published by . This book was released on 1888 with total page 925 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Numerical Study of Shock induced Combustion in Methane air Mixtures

Download or read book Numerical Study of Shock induced Combustion in Methane air Mixtures written by Shaye Yungster and published by . This book was released on 1993 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Numerical Simulation of Scramjet Combustion in a Shock Tunnel

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.

Book Numerical Simulation of Unsteady Normal Detonation Combustion

Download or read book Numerical Simulation of Unsteady Normal Detonation Combustion written by Ajjay Omprakas and published by . This book was released on 2019 with total page 79 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this research is to simulate normal detonation combustion which is a mode of operation for a Pulsed Detonation Engine (PDE). A supersonic flow with stoichiometric hydrogen-air mixture is made to impinge on a wedge, thus resulting in increasing the temperature and pressure across a shock wave leading to the formation of detonation wave. Different modes of the operations can be simulated by varying the incoming Mach number, pressure, temperature and equivalence ratio. For the case of normal detonation wave mode which is an unsteady process, after the detonation being initiated due to the shock induced by the wedge, the detonation wave propagates upstream in the flow as the combustion chamber Mach number is lower than the C-J Mach number. The concept of detonation wave moving upstream and downstream is controlled by changing the incoming flow field properties. By this method the unsteady normal detonation wave is made to oscillate in the combustion chamber leading to a continuous detonation combustion. The intention of this research is to simulate two cycles of detonation combustion in order to determine the frequency and to obtain the variation of flow properties at the exit plain with respect to time.

Book Numerical Simulation of Hypersonic Shock induced Combustion Ramjet Flowfields microform

Download or read book Numerical Simulation of Hypersonic Shock induced Combustion Ramjet Flowfields microform written by Rudy Dudebout and published by National Library of Canada = Bibliothèque nationale du Canada. This book was released on 1996 with total page 568 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Towards a Numerical Simulation of Supersonic Mixing Combustion

Download or read book Towards a Numerical Simulation of Supersonic Mixing Combustion written by Mohammed Kamel and published by LAP Lambert Academic Publishing. This book was released on 2013 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt: The design and off-design studies of the hypersonic air-breathing engines face many challenges, due to the complexity of their internal flows. The mixing and combustion processes in Supersonic-Combustion Ramjet (scramjet) engines involve complicated aerothermochemical features, such as: the interactions between shock-waves and boundary-layer, the shock induced-combustion and the recirculation zones. In this study, a numerical solver is developed and validated to be an efficient design tool capable of simulating these complicated flow features of the supersonic combustors. For the code validation, several test cases are considered to monitor the code ability to solve for the diffusive and turbulent fluxes, and the chemical source term. In addition, the code is validated by resolving the transverse sonic injection into supersonic air flow in the case of Helium injection from a flat plate, and in the case of Hydrogen injection in a single-strut scramjet engine. The effectiveness of this injection technique in mixing and flame-holding is demonstrated. The results show good agreement with the previous numerical and experimental investigations, and prove the simulator's accuracy.