Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722277598 Category : Languages : en Pages : 38
Book Description
A class of implicit Total Variation Diminishing (TVD) type algorithms suitable for transonic and supersonic multidimensional Euler and Navier-Stokes equations was extended to hypersonic computations. The improved conservative shock-capturing schemes are spatially second- and third-order, and are fully implicit. They can be first- or second-order accurate in time and are suitable for either steady or unsteady calculations. Enhancement of stability and convergence rate for hypersonic flows is discussed. With the proper choice of the temporal discretization and suitable implicit linearization, these schemes are fairly efficient and accurate for very complex two-dimensional hypersonic inviscid and viscous shock interactions. This study is complimented by a variety of steady and unsteady viscous and inviscid hypersonic blunt-body flow computations. Due to the inherent stiffness of viscous flow problems, numerical experiments indicated that the convergence rate is in general slower for viscous flows than for inviscid steady flows. Yee, H. C. and Klopfer, G. H. and Montagne, J.-L. Ames Research Center ...
Author: Norbert Kroll Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 68
Book Description
A comparative study of five upwind schemes was performed to evaluate their ability accurately model the convective fluxes of the Euler equations for problems containing complex shock structure. The schemes investigated used a variety of Reimann solvers and obtained higher order accuracy using either a MUSCL or non-MUSCL approach. The MUSCL-type schemes included the flux vector split formulations of Steiger-Warming and van Leer and the flux difference split approach of Roe. The Non-MUSCL schemes included the Symmetric and Upwind TVD methods of Yee, and Harten and Yee. Two central difference schemes provide a basis for the evaluation of these upwind methods. The comparison was performed using identical meshes and convergence criteria. In a supersonic blunt body flow, all the upwind schemes displayed comparably resolved bow shocks, independent of free stream Mach number. However, a complex type IV shock on cowl lip example pointed out significant difference in the accuracy and convergence behavior of the schemes. A comparison of the flow structure shown by the various algorithms on identical grids indicated that the discrete solutions obtained with Upwind TVD and Roe flux difference splitting were the least diffusive of the upwind methods considered.
Author: Datta V. Gaitonde Publisher: ISBN: Category : Aerodynamics, Hypersonic Languages : en Pages : 64
Book Description
The interaction of an impinging shock with the bow-shock generated by a blunt geometry is examined numerically for hypersonic (Mach 8, perfect gas) flows with modified Steger-Warming flux-split scheme. The modifications are designed to reduce numerical dissipation in the boundary layer thus improving the resolution and accuracy of the resulting algorithm. The full 2-D Navier- Stokes equations are solved in finite-volume formulation with central differencing for viscous terms and residual driven line Gauss-Seidel relaxation for time advancement. Grid resolution studies are performed. For a Type IV interaction, comparison with surface pressure and heat-transfer rates display good overall agreement with experimental values. For a Type III+ interaction, a detailed comparison is made with experimental surface quantities and a computation with Van Leer's flux-splitting algorithm. The peak amplification of pressure is modestly overpredicted with the current algorithm. The computed peak heat transfer is comparable to that obtained in previous research with Van Leer's splitting, although anomalous behavior is observed in the vicinity of the stagnation point. This behavior may be eliminated with appropriate corrections.
Author: Konstantinos Kontis Publisher: Springer Science & Business Media ISBN: 3642256856 Category : Science Languages : en Pages : 1122
Book Description
The University of Manchester hosted the 28th International Symposium on Shock Waves between 17 and 22 July 2011. The International Symposium on Shock Waves first took place in 1957 in Boston and has since become an internationally acclaimed series of meetings for the wider Shock Wave Community. The ISSW28 focused on the following areas: Blast Waves, Chemically Reacting Flows, Dense Gases and Rarefied Flows, Detonation and Combustion, Diagnostics, Facilities, Flow Visualisation, Hypersonic Flow, Ignition, Impact and Compaction, Multiphase Flow, Nozzle Flow, Numerical Methods, Propulsion, Richtmyer-Meshkov, Shockwave Boundary Layer Interaction, Shock Propagation and Reflection, Shock Vortex Interaction, Shockwave Phenomena and Applications, as well as Medical and Biological Applications. The two Volumes contain the papers presented at the symposium and serve as a reference for the participants of the ISSW 28 and individuals interested in these fields.
Author: National Aeronautics and Space Administration (NASA)
Author: 
Author: 
Author: Norbert Kroll
Author: Datta V. Gaitonde
Author: 
Author: Goetz H. Klopfer
Author: Konstantinos Kontis
Author: 
Author: