Modeling of Energy Transfer in Hypersonic Shocks Using High Fidelity Models

Modeling of Energy Transfer in Hypersonic Shocks Using High Fidelity Models PDF Author: Tong Zhu
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Book Description
The spectra of high-temperature, chemically reacting hypersonic flows provides the most powerful diagnostic available for testing thermochemically nonequilibrium models in re-entry conditions. Several shock tube experiments have revealed that conventional phenomenological approach can not accurately predict the internal temperature of the gas and also the corresponding radiation.In particular, large rotational nonequilibrium in strong shocks has been observed in several experiments with high peak translational temperatures. The Direct Simulation Monte Carlo (DSMC) method is a particle-based simulation method that is capable of properly simulating flows with large nonequilibrium. In the experiments above, one dimensional shocks are most widely studied but they are challenging to simulate using the DSMC method due to the unsteady nature of the flows and especially for hypersonic flows with chemical reactions taking place. Therefore, efficient approaches for simulating one-dimensional shocks are developed for use in DSMC simulations.Both a shock stabilization technique and a modified DSMC unsteady sampling approach are used in simulating one dimensional, unsteady shocks. In the latter approach, a moving sampling region is used to obtain an accurate profile of the reflected shock in air. The shock number density and temperature profiles are obtained and used to calculate excitation and radiation. The Quasi-Steady-State (QSS) assumption is made in the excitation calculation where both electron impact and heavy particle impact excitation for the NO(A) and the N2+(B) states are studied. The calculated NO radiation in the wavelength range of lambda = 235+/-7nm for shock speeds below 7km/s are in good agreement with the experiment, but, the predicted radiation is lower than the experiment for shock speeds above 7km/s. In addition, the N2+ radiation in the wavelength range of lambda = 391.4+/-0.2nm are in good agreement with the experimental data for shock speeds above 9km/s. High fidelity models for simulating both the dissociation and relaxation processes in N+N2 and N2+N2 systems are also investigated. Relaxation cross sections are computed and the 99 bin method shows good agreement between the bin-to-bin and state specific relaxation cross sections for both N-N2 and N2-N2 relaxation. These relaxation cross sections are then implemented separately in 0D DSMC isothermal relaxation cases. For both cases, the rotational and vibrational temperatures relax to the equilibrium heat bath temperature. For N-N2 relaxations, the rotational temperature relaxes faster than the vibrational temperature at relatively low translational temperature and at a very similar rate to the vibrational temperature at relatively high temperature. These are in qualitative agreement with the observation of earlier experiments. The one-dimensional binning method and associated cross sections by Parsons et al. are implemented in DSMC simulations and the results are compared with those using the traditional TCE and LB models. For shock conditions similar to those in the experiments of Gorelov, it is found that the MD-QCT chemical reaction model predicts more dissociation and faster relaxation of the vibrational temperature. In the higher speed shock condition of the experiment by Fujita, the use of MD-QCT databases for both chemical reaction and internal energy predicts more dissociation in the downstream of the shock but slower relaxation of the rotational temperature. Also the rotational temperature in the shock region is in somewhat better agreement with the experiment of Fujita.

Modeling of Energy Transfer in Hypersonic Shocks Using High Fidelity Models

Modeling of Energy Transfer in Hypersonic Shocks Using High Fidelity Models PDF Author: Tong Zhu
Publisher:
ISBN:
Category :
Languages : en
Pages :

Get Book Here

Book Description
The spectra of high-temperature, chemically reacting hypersonic flows provides the most powerful diagnostic available for testing thermochemically nonequilibrium models in re-entry conditions. Several shock tube experiments have revealed that conventional phenomenological approach can not accurately predict the internal temperature of the gas and also the corresponding radiation.In particular, large rotational nonequilibrium in strong shocks has been observed in several experiments with high peak translational temperatures. The Direct Simulation Monte Carlo (DSMC) method is a particle-based simulation method that is capable of properly simulating flows with large nonequilibrium. In the experiments above, one dimensional shocks are most widely studied but they are challenging to simulate using the DSMC method due to the unsteady nature of the flows and especially for hypersonic flows with chemical reactions taking place. Therefore, efficient approaches for simulating one-dimensional shocks are developed for use in DSMC simulations.Both a shock stabilization technique and a modified DSMC unsteady sampling approach are used in simulating one dimensional, unsteady shocks. In the latter approach, a moving sampling region is used to obtain an accurate profile of the reflected shock in air. The shock number density and temperature profiles are obtained and used to calculate excitation and radiation. The Quasi-Steady-State (QSS) assumption is made in the excitation calculation where both electron impact and heavy particle impact excitation for the NO(A) and the N2+(B) states are studied. The calculated NO radiation in the wavelength range of lambda = 235+/-7nm for shock speeds below 7km/s are in good agreement with the experiment, but, the predicted radiation is lower than the experiment for shock speeds above 7km/s. In addition, the N2+ radiation in the wavelength range of lambda = 391.4+/-0.2nm are in good agreement with the experimental data for shock speeds above 9km/s. High fidelity models for simulating both the dissociation and relaxation processes in N+N2 and N2+N2 systems are also investigated. Relaxation cross sections are computed and the 99 bin method shows good agreement between the bin-to-bin and state specific relaxation cross sections for both N-N2 and N2-N2 relaxation. These relaxation cross sections are then implemented separately in 0D DSMC isothermal relaxation cases. For both cases, the rotational and vibrational temperatures relax to the equilibrium heat bath temperature. For N-N2 relaxations, the rotational temperature relaxes faster than the vibrational temperature at relatively low translational temperature and at a very similar rate to the vibrational temperature at relatively high temperature. These are in qualitative agreement with the observation of earlier experiments. The one-dimensional binning method and associated cross sections by Parsons et al. are implemented in DSMC simulations and the results are compared with those using the traditional TCE and LB models. For shock conditions similar to those in the experiments of Gorelov, it is found that the MD-QCT chemical reaction model predicts more dissociation and faster relaxation of the vibrational temperature. In the higher speed shock condition of the experiment by Fujita, the use of MD-QCT databases for both chemical reaction and internal energy predicts more dissociation in the downstream of the shock but slower relaxation of the rotational temperature. Also the rotational temperature in the shock region is in somewhat better agreement with the experiment of Fujita.

Advances in Hypersonics

Advances in Hypersonics PDF Author: Bertin
Publisher: Springer Science & Business Media
ISBN: 1461203716
Category : Science
Languages : en
Pages : 280

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Book Description
These three volumes entitled Advances in Hypersonics contain the Proceedings of the Second and Third Joint US/Europe Short Course in Hypersonics which took place in Colorado Springs and Aachen. The Second Course was organized at the US Air Force Academy, USA in January 1989 and the Third Course at Aachen, Germany in October 1990. The main idea of these Courses was to present to chemists, com puter scientists, engineers, experimentalists, mathematicians, and physicists state of the art lectures in scientific and technical dis ciplines including mathematical modeling, computational methods, and experimental measurements necessary to define the aerothermo dynamic environments for space vehicles such as the US Orbiter or the European Hermes flying at hypersonic speeds. The subjects can be grouped into the following areas: Phys ical environments, configuration requirements, propulsion systems (including airbreathing systems), experimental methods for external and internal flow, theoretical and numerical methods. Since hyper sonic flight requires highly integrated systems, the Short Courses not only aimed to give in-depth analysis of hypersonic research and technology but also tried to broaden the view of attendees to give them the ability to understand the complex problem of hypersonic flight. Most of the participants in the Short Courses prepared a docu ment based on their presentation for reproduction in the three vol umes. Some authors spent considerable time and energy going well beyond their oral presentation to provide a quality assessment of the state of the art in their area of expertise as of 1989 and 1991.

The Influence of Dissipative Numerics on Shock Interaction Modeling for Hypersonic Flows

The Influence of Dissipative Numerics on Shock Interaction Modeling for Hypersonic Flows PDF Author: Will J. Stoffers
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 52

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Book Description
This paper presents a low order simulation of a hypersonic shock tunnel experiment at the Calspan-University at Buffalo Research Center (CUBRC). In this experiment, a relatively low enthalpy flow is passed over a double cone geometry at a speed near Mach 12. Empirical data is taken and a higher order simulation of the experiment is also used for comparison. The present study compares the low fidelity data (first order spatial reconstruction) against the empirical and higher fidelity data (second order reconstruction) for this flow. A large difference in separation zone length is evident between the high and low order simulations when pressure and heat transfer are plotted. This confirms the dissipative nature of low order numerical schemes. An evaluation of chemistry models is made as well, comparing the Park model with Kang & Dunn's. Little difference is observed between the low order Park results and the low order Kang & Dunn data. The Kang & Dunn model is chosen because it requires fewer computational resources.

DSMC Modeling of Vibration-translation Energy Transfer in Hypersonic Rarefied Flows

DSMC Modeling of Vibration-translation Energy Transfer in Hypersonic Rarefied Flows PDF Author: S. F. Gimelshein
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Advances in Hypersonics

Advances in Hypersonics PDF Author: BERTIN
Publisher: Springer Science & Business Media
ISBN: 1461203759
Category : Technology & Engineering
Languages : en
Pages : 438

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Book Description
These three volumes entitled Advances in Hypersonics contain the Proceedings of the Second and Third Joint US/Europe Short Course in Hypersonics which took place in Colorado Springs and Aachen. The Second Course was organized at the US Air Force Academy, USA in January 1989 and the Third Course at Aachen, Germany in October 1990. The main idea of these Courses was to present to chemists, com puter scientists, engineers, experimentalists, mathematicians, and physicists state of the art lectures in scientific and technical dis ciplines including mathematical modeling, computational methods, and experimental measurements necessary to define the aerothermo dynamic environments for space vehicles such as the US Orbiter or the European Hermes flying at hypersonic speeds. The subjects can be grouped into the following areas: Phys ical environments, configuration requirements, propulsion systems (including airbreathing systems), experimental methods for external and internal flow, theoretical and numerical methods. Since hyper sonic flight requires highly integrated systems, the Short Courses not only aimed to give in-depth analysis of hypersonic research and technology but also tried to broaden the view of attendees to give them the ability to understand the complex problem of hypersonic flight. Most of the participants in the Short Courses prepared a docu ment based on their presentation for reproduction in the three vol umes. Some authors spent considerable time and energy going well beyond their oral presentation to provide a quality assessment of the state of the art in their area of expertise as of 1989 and 1991.

Semi-Analytical Modeling of Shock-wave/Boundary Layer Interaction Over Compression Ramps in Hypersonic Flow

Semi-Analytical Modeling of Shock-wave/Boundary Layer Interaction Over Compression Ramps in Hypersonic Flow PDF Author: Ryan Glenn
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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Book Description
The understanding of hypersonic flow is critical for bodies--such as rockets and missiles--traveling significantly faster than the speed of sound. One of the under-resolved flow phenomena in hypersonic flow is the Shock Wave/Boundary Layer Interaction (SWBLI), which may significantly impact the aerothermal loads on vehicle structures. The high-fidelity modeling of SWBLI is computationally intensive and typically intractable for vehicle design and optimization purposes. The ultimate goal of this research is to develop an accurate and computationally efficient semi-analytical model for the SWBLI over compression ramps. As a first step, the semi-analytical model is developed using the shock/expansion wave theory and minimum dissipation principle to estimate the pressure on the compression ramp. Using the developed semi-analytical model, the effect of the ramp angle on the SWBLI is examined. Eventually, the model could enable the aeroelastic analysis and optimization of hypersonic structures with sufficient fidelity and high computational efficiency.

National Academy of Sciences’ decadal plan for aeronautics : hearings

National Academy of Sciences’ decadal plan for aeronautics : hearings PDF Author:
Publisher: DIANE Publishing
ISBN: 9781422322444
Category :
Languages : en
Pages : 440

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Book Description


Advances in Hypersonics

Advances in Hypersonics PDF Author: 3Island Press
Publisher:
ISBN: 9781461203728
Category :
Languages : en
Pages : 284

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Book Description


Aerothermodynamic Calculations on X-34 at Mach 6 Wind Tunnel Conditions

Aerothermodynamic Calculations on X-34 at Mach 6 Wind Tunnel Conditions PDF Author: William A. Wood
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 26

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Book Description


Hypersonic and High Temperature Gas Dynamics

Hypersonic and High Temperature Gas Dynamics PDF Author: John David Anderson
Publisher: AIAA
ISBN: 9781563474590
Category : Science
Languages : en
Pages : 710

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Book Description
This book is a self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics. It assumes no prior familiarity with either subject on the part of the reader. If you have never studied hypersonic and/or high-temperature gas dynamics before, and if you have never worked extensively in the area, then this book is for you. On the other hand, if you have worked and/or are working in these areas, and you want a cohesive presentation of the fundamentals, a development of important theory and techniques, a discussion of the salient results with emphasis on the physical aspects, and a presentation of modern thinking in these areas, then this book is also for you. In other words, this book is designed for two roles: 1) as an effective classroom text that can be used with ease by the instructor, and understood with ease by the student; and 2) as a viable, professional working tool for engineers, scientists, and managers who have any contact in their jobs with hypersonic and/or high-temperature flow.