Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Hypersonic Maneuvering Vehicle Simulations Using Real Aas Unstructured Navier Stokes Software
Download Hypersonic Maneuvering Vehicle Simulations Using Real Aas Unstructured Navier Stokes Software full books in PDF, epub, and Kindle. Read online Hypersonic Maneuvering Vehicle Simulations Using Real Aas Unstructured Navier Stokes Software ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Hypersonic Maneuvering Vehicle Simulations Using Real-aas, Unstructured Navier-Stokes Software by : William D. McGrory
Download or read book Hypersonic Maneuvering Vehicle Simulations Using Real-aas, Unstructured Navier-Stokes Software written by William D. McGrory and published by . This book was released on 2001 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonic vehicles are becoming more of a reality with the current level of technology. Concept vehicles are now being made in order to test the most recent advances in hypersonic technology. Along with models for flight testing, CFD has become an important role in the development of modern hypersonic vehicles. The technology in CFD is making more complex configurations and flow-fields available for simulation. One of the advances in CFD that is making this possible is unstructured grid generation and flow solvers.
Book Synopsis Hypersonic Maneuvering Vehicle Simulations Using Real-Gas, Unstructured Navier-Stokes Software by :
Download or read book Hypersonic Maneuvering Vehicle Simulations Using Real-Gas, Unstructured Navier-Stokes Software written by and published by . This book was released on 2001 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonic vehicles are becoming more of a reality with the current level of technology. Concept vehicles are now being made in order to test the most recent advances in hypersonic technology. Along with models for flight testing, CFD has become an important role in the development of modern hypersonic vehicles. The technology in CFD is making more complex configurations and flow-fields available for simulation. One of the advances in CFD that is making this possible is unstructured grid generation and flow solvers.
Book Synopsis Advances in Some Hypersonic Vehicles Technologies by : Ramesh K. Agarwal
Download or read book Advances in Some Hypersonic Vehicles Technologies written by Ramesh K. Agarwal and published by BoD – Books on Demand. This book was released on 2018-03-14 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book describes the recent progress in some hypersonic technologies such as the aerodynamic modeling and numerical simulations of rarefied flows, boundary layer receptivity, coupled aerodynamics, and heat transfer problems, including fluid-thermal-structure interactions and launcher aerodynamic design as well as other miscellaneous topics, such as porous ceramic composite phase change control system and vehicle profile, following LQR design. Both the researchers and the students should find the material useful in their work.
Book Synopsis Assessment of Reduced Fidelity Modeling of a Maneuvering Hypersonic Vehicle by : Emily Rose Dreyer
Download or read book Assessment of Reduced Fidelity Modeling of a Maneuvering Hypersonic Vehicle written by Emily Rose Dreyer and published by . This book was released on 2021 with total page 117 pages. Available in PDF, EPUB and Kindle. Book excerpt: Balancing accurate and efficient estimation of aerothermodynamic loads is a significant challenge for multi-disciplinary modeling and analysis of high speed vehicles. High fidelity methods are desired in order to minimize modeling uncertainty. However, the need for either online aerothermodynamic modeling or many model iterations often introduces a hard constraint on model run-time that favors the use of classical engineering methods. Thus, systematic characterization of trade-offs in accuracy and run-time costs for different levels of modeling fidelity is a critical need. Technical challenges toward this need include the wide range of operating conditions and parameters associated with a complete vehicle, as well as the inability to comprehensively assess hypersonic configurations in ground-based facilities. The goal of this dissertation is to systematically study a range of reduced fidelity aerothermodynamics models in order to determine relevant fidelity. This is carried out by first examining the impact of analytical and data-driven model reductions over a broad parameter space in the context of steady-state aerothermodynamic loads. This work builds on previous by extending existing approaches to accommodate a complete three-dimensional hypersonic geometry. Three models for pressure are investigated: two of the models are kriging interpolants of either Reynolds-averaged Navier-Stokes (RANS) or Euler computational fluid dynamics (CFD) data, and the third is a shock-expansion model. Four models for heat flux are investigated: a kriging interpolant of RANS CFD; an Eckert's reference temperature model using a kriging interpolant of RANS CFD pressure; an Eckert's reference temperature model using kriging interpolants of Euler CFD pressure and temperature; and an Eckert's reference temperature model using shock-expansion theory pressure and temperature. The reduced models are compared to RANS CFD predictions on the surface of a complete hypersonic vehicle over a broad operational space. The results and conclusions highlighted trade-offs in the context of accuracy and computational requirements for different types of loads models for use in multi-disciplinary simulations of high-speed vehicles. The second part of this work explores the degree of unsteadiness in integrated aerodynamic loads at representative reduced frequencies for a pitching vehicle. A typical approach is to assume unsteady aerodynamic loads as either steady-state or quasi-steady. The former assumes that the aerodynamic loads only depend on the instantaneous inclination angle, while the latter includes a pressure perturbation due to an induced inclination angle from surface velocity. Unsteadiness in integrated aerodynamic loads is assessed at the component level and on a complete vehicle with and without viscous effects. Results indicate that both unsteadiness and the importance of viscosity in integrated aerodynamic loads increase with three-dimensionality of the flow. Three-dimensionality enhances load hysteresis due to flow unsteadiness, while fin-body flow interactions are found to increase the lift-curve slope of the dynamically pitching vehicle. Compared to a control surface in isolation, viscosity has a strong, albeit complex, influence on deviations of fully unsteady loads models from quasi-steady and steady models. The precise mechanisms that drive a relatively rapid divergence from quasi-steady flow for the complete vehicle remain inadequately understood and additional study is needed.
Book Synopsis Nonequilibrium Hypersonic Aerothermodynamics Using the Direct Simulation Monte Carlo And Navier-Stokes Models by :
Download or read book Nonequilibrium Hypersonic Aerothermodynamics Using the Direct Simulation Monte Carlo And Navier-Stokes Models written by and published by . This book was released on 2008 with total page 262 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonic flight vehicles are a current topic of interest in both civilian and military research. NASA is currently designing a Crew Transport Vehicle (CTV) [44, 69] and Crew Exploration Vehicle (CEV) [32] to replace the space shuttle; reentry vehicles are, by definition, hypersonic vehicles. Military requirements for reconnaissance and surveillance, as well as the mission of the United States Air Force to rapidly project power globally makes the design of a hypersonic plane that can quickly traverse the globe very attractive [102]. The design of hypersonic vehicles requires accurate prediction of the surface properties while in flight. These quantities are typically the heat flux, pressure and shear stress, from which the aerodynamic forces and moments can be calculated. These variables govern not only the aerodynamic performance of the vehicle, but also determine the selection and sizing of the thermal protection system (TPS), which protects the vehicle from the extreme temperatures encountered at hypersonic velocities. The geometry of a vehicle, and in particular, the nose and the leading edges of wings and other aerodynamic surfaces, is a critical consideration in a vehicle's design. Aerodynamic heating is inversely proportional to the square root of the 1 radius at the stagnation point; hence, historically most vehicles have had blunted noses and leading edges to reduce the thermal loads to acceptable levels. Recently, however, a class of materials, designated Ultra-High Temperature Ceramic (UHTC) composites, has been developed that can withstand temperatures as high as 3500 K [57, 78]. Materials such as these allow the use of much sharper leading edges.
Book Synopsis Development of a Non-Linear Simulation for Generic Hypersonic Vehicles - Asuhs1 by : National Aeronautics and Space Adm Nasa
Download or read book Development of a Non-Linear Simulation for Generic Hypersonic Vehicles - Asuhs1 written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-02 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: A nonlinear simulation is developed to model the longitudinal motion of a vehicle in hypersonic flight. The equations of motion pertinent to this study are presented. Analytic expressions for the aerodynamic forces acting on a hypersonic vehicle which were obtained from Newtonian Impact Theory are further developed. The control surface forces are further examined to incorporate vehicle elastic motion. The purpose is to establish feasible equations of motion which combine rigid body, elastic, and aeropropulsive dynamics for use in nonlinear simulations. The software package SIMULINK is used to implement the simulation. Also discussed are issues needing additional attention and potential problems associated with the implementation (with proposed solutions). Salas, Juan and Lovell, T. Alan and Schmidt, David K. Unspecified Center...
Book Synopsis Launch Vehicle Simulations Using a Concurrent, Implicit Navier-Stokes Solver by : Stephen Taylor
Download or read book Launch Vehicle Simulations Using a Concurrent, Implicit Navier-Stokes Solver written by Stephen Taylor and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Hypersonic Vehicle Environment Simulation. Phase 1 by :
Download or read book Hypersonic Vehicle Environment Simulation. Phase 1 written by and published by . This book was released on 1989 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt: The hypersonic, viscous, chemically reacting flow around a vehicle in the upper layers of the atmosphere influences vehicle performance, thermal environment, and sensor visibility. Under the Phase I effort; a unique hybrid Navier-Stokes/Monte Carlo method has been successfully developed for the simulation of said hypersonic flows. This method combines a continuum description of the gas mixture with a statistical (or particle) description of the species transport and the chemical reactions, thereby allowing easy use of available chemical kinetics data. As such, the hybrid approach is capable of exploiting both the efficiency of a continuum approach for the fluid dynamic calculations and the benefits in physical modeling of the Monte Carlo approach for chemical reactions. The viability of this hybrid approach for practical hypersonic flow calculations has been demonstrated in the Phase I effort via the calculation of the chemically reacting flow field over an axisymmetric cone. A proposed Phase II effort would continue the development of this method by improving the numerical efficiency of the particle transport scheme, and by incorporating physical models for catalytic walls, recombination reactions, and ionization. In addition, radiation would be included via a radiation transport model. For the class of problems of interest here, the resulting procedure will be able to represent the complex chemical and thermal processes occurring around a hypersonic vehicle in much more detail than is currently possible with either the continuum or the direct simulation Monte Carlo (DSMC) approach.
Book Synopsis Computation of Hypersonic Flow about Maneuvering Vehicles with Changing Shapes by :
Download or read book Computation of Hypersonic Flow about Maneuvering Vehicles with Changing Shapes written by and published by . This book was released on 2004 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Vehicles moving at hypersonic speeds have great importance to the National Security. Ballistic missile re-entry vehicles (RV's) travel at hypersonic speeds, as do missile defense intercept vehicles. Despite the importance of the problem, no computational analysis method is available to predict the aerodynamic environment of maneuvering hypersonic vehicles, and no analysis is available to predict the transient effects of their shape changes. The present state-of-the-art for hypersonic flow calculations typically still considers steady flow about fixed shapes. Additionally, with present computational methods, it is not possible to compute the entire transient structural and thermal loads for a re-entry vehicle. The objective of this research is to provide the required theoretical development and a computational analysis tool for calculating the hypersonic flow about maneuvering, deforming RV's. This key enabling technology will allow the development of a complete multi-mechanics simulation of the entire RV flight sequence, including important transient effects such as complex flight dynamics. This will allow the computation of the as-delivered state of the payload in both normal and unusual operational environments. This new analysis capability could also provide the ability to predict the nonlinear, transient behavior of endo-atmospheric missile interceptor vehicles to the input of advanced control systems. Due to the computational intensity of fluid dynamics for hypersonics, the usual approach for calculating the flow about a vehicle that is changing shape is to complete a series of steady calculations, each with a fixed shape. However, this quasi-steady approach is not adequate to resolve the frequencies characteristic of a vehicle's structural dynamics. Our approach is to include the effects of the unsteady body shape changes in the finite-volume method by allowing for arbitrary translation and deformation of the control volumes. Furthermore, because the Eulerian computational mesh for the fluid domain must be attached to the vehicle as it undergoes potentially high accelerations, that mesh must be viewed in a non-inertial coordinate frame. The usual conservation-law form of the fluid dynamic governing equations must be augmented. This approach thus requires the derivation of a significantly new numerical formulation, especially to incorporate a modern flux-splitting methodology as needed for numerical stability and accuracy.
Book Synopsis Facing the Heat Barrier by : T. A. Heppenheimer
Download or read book Facing the Heat Barrier written by T. A. Heppenheimer and published by Government Printing Office. This book was released on 2009-08 with total page 358 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonics is the study of flight at speeds where aerodynamic heating dominates the physics of the problem. It is an engineering science with close links to supersonics and engine design. Within this field, many of the most important results have been experimental. The principal facilities have been wind tunnels and related devices, which have produced flows with speeds up to orbital velocity. Why is this important? Hypersonics has had two major applications. The first has been to provide thermal protection during atmospheric reentry. Success in this enterprise has supported ballistic-missile nose cones, has returned strategic reconnaissance photos from orbit and astronauts from the Moon, and has even dropped an instrument package into the atmosphere of Jupiter. The second application has involved high-speed propulsion and has sought to develop the scramjet as an advanced airbreathing ramjet. Atmospheric entry today is fully mature as an engineering discipline, but work with its applications continues to reach for new achievements. Studies of scramjets still seek full success, in which such engines can accelerate a vehicle without the use of rockets. Hence, there is much to do in this area as well.
Book Synopsis Computational Fluid Dynamics by : Jiri Blazek
Download or read book Computational Fluid Dynamics written by Jiri Blazek and published by Elsevier. This book was released on 2005-12-20 with total page 491 pages. Available in PDF, EPUB and Kindle. Book excerpt: Computational Fluid Dynamics (CFD) is an important design tool in engineering and also a substantial research tool in various physical sciences as well as in biology. The objective of this book is to provide university students with a solid foundation for understanding the numerical methods employed in today’s CFD and to familiarise them with modern CFD codes by hands-on experience. It is also intended for engineers and scientists starting to work in the field of CFD or for those who apply CFD codes. Due to the detailed index, the text can serve as a reference handbook too. Each chapter includes an extensive bibliography, which provides an excellent basis for further studies.
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 934 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA SP. written by and published by . This book was released on 1992 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Unsteady Computational Fluid Dynamics in Aeronautics by : P.G. Tucker
Download or read book Unsteady Computational Fluid Dynamics in Aeronautics written by P.G. Tucker and published by Springer Science & Business Media. This book was released on 2013-08-30 with total page 432 pages. Available in PDF, EPUB and Kindle. Book excerpt: The field of Large Eddy Simulation (LES) and hybrids is a vibrant research area. This book runs through all the potential unsteady modelling fidelity ranges, from low-order to LES. The latter is probably the highest fidelity for practical aerospace systems modelling. Cutting edge new frontiers are defined. One example of a pressing environmental concern is noise. For the accurate prediction of this, unsteady modelling is needed. Hence computational aeroacoustics is explored. It is also emerging that there is a critical need for coupled simulations. Hence, this area is also considered and the tensions of utilizing such simulations with the already expensive LES. This work has relevance to the general field of CFD and LES and to a wide variety of non-aerospace aerodynamic systems (e.g. cars, submarines, ships, electronics, buildings). Topics treated include unsteady flow techniques; LES and hybrids; general numerical methods; computational aeroacoustics; computational aeroelasticity; coupled simulations and turbulence and its modelling (LES, RANS, transition, VLES, URANS). The volume concludes by pointing forward to future horizons and in particular the industrial use of LES. The writing style is accessible and useful to both academics and industrial practitioners. From the reviews: "Tucker's volume provides a very welcome, concise discussion of current capabilities for simulating and modellng unsteady aerodynamic flows. It covers the various pos sible numerical techniques in good, clear detail and presents a very wide range of practical applications; beautifully illustrated in many cases. This book thus provides a valuable text for practicing engineers, a rich source of background information for students and those new to this area of Research & Development, and an excellent state-of-the-art review for others. A great achievement." Mark Savill FHEA, FRAeS, C.Eng, Professor of Computational Aerodynamics Design & Head of Power & Propulsion Sciences, Department of Power & Propulsion, School of Engineering, Cranfield University, Bedfordshire, U.K. "This is a very useful book with a wide coverage of many aspects in unsteady aerodynamics method development and applications for internal and external flows." L. He, Rolls-Royce/RAEng Chair of Computational Aerothermal Engineering, Oxford University, U.K. "This comprehensive book ranges from classical concepts in both numerical methods and turbulence modelling approaches for the beginner to latest state-of-the-art for the advanced practitioner and constitutes an extremely valuable contribution to the specific Computational Fluid Dynamics literature in Aeronautics. Student and expert alike will benefit greatly by reading it from cover to cover." Sébastien Deck, Onera, Meudon, France
Download or read book Aeronautical Engineering written by and published by . This book was released on 1992 with total page 648 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 Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 274) by :
Download or read book Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 274) written by and published by . This book was released on 1992 with total page 648 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :Ernst Heinrich Hirschel Publisher :Springer Science & Business Media ISBN 13 :3540265198 Total Pages :419 pages Book Rating :4.5/5 (42 download)
Book Synopsis Basics of Aerothermodynamics by : Ernst Heinrich Hirschel
Download or read book Basics of Aerothermodynamics written by Ernst Heinrich Hirschel and published by Springer Science & Business Media. This book was released on 2006-01-16 with total page 419 pages. Available in PDF, EPUB and Kindle. Book excerpt: The last two decades have brought two important developments for aeroth- modynamics. One is that airbreathing hypersonic flight became the topic of technology programmes and extended system studies. The other is the emergence and maturing of the discrete numerical methods of aerodyn- ics/aerothermodynamics complementary to the ground-simulation facilities, with the parallel enormous growth of computer power. Airbreathing hypersonic flight vehicles are, in contrast to aeroassisted re-entry vehicles, drag sensitive. They have, further, highly integrated lift and propulsion systems. This means that viscous eflFects, like boundary-layer development, laminar-turbulent transition, to a certain degree also strong interaction phenomena, are much more important for such vehicles than for re-entry vehicles. This holds also for the thermal state of the surface and thermal surface effects, concerning viscous and thermo-chemical phenomena (more important for re-entry vehicles) at and near the wall. The discrete numerical methods of aerodynamics/aerothermodynamics permit now - what was twenty years ago not imaginable - the simulation of high speed flows past real flight vehicle configurations with thermo-chemical and viscous effects, the description of the latter being still handicapped by in sufficient flow-physics models. The benefits of numerical simulation for flight vehicle design are enormous: much improved aerodynamic shape definition and optimization, provision of accurate and reliable aerodynamic data, and highly accurate determination of thermal and mechanical loads. Truly mul- disciplinary design and optimization methods regarding the layout of thermal protection systems, all kinds of aero-servoelasticity problems of the airframe, et cetera, begin now to emerge.
