3 edition of Numerical calculation of subsonic jets in crossflow with reduced numerical diffusion found in the catalog.
Numerical calculation of subsonic jets in crossflow with reduced numerical diffusion
|Statement||Russell W. Claus.|
|Series||NASA technical memorandum -- 87003.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
view to simulate the tip-vortex formation in subsonic and transonic flows. 2. Governing Equations and Numerical Scheme At the Reynolds numbers of interest in the present calculations, the flow on the wing can be considered to be mostly inviscid except in a small region near the body surface where the viscous effects are important. An investigation of subsonic transverse jet injection into a subsonic vitiated crossflow is discussed. The reacting jet in crossflow (RJIC) system investigated as a means of secondary injection of fuel in a staged combustion system. The measurements were performed in test rigs featuring (a) a steady, swirling crossflow and (b) a crossflow with. Numerical simulations of the ballistic diode using the hydrodynamic device model are presented, as an illustrative elliptic problem. The im- portance of nonlinear block iterative methods is emphasized. Argu- ments for existence of solutions and convergence of numerical methods are given for the case of subsonic electron flow. I. INTRODUCTION T.
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Get this from a library. Numerical calculation of subsonic jets in crossflow with reduced numerical diffusion. [Russell W Claus; United States. National Aeronautics and Space Administration.]. Numerical calculation of subsonic jets in crossflow with reduced numerical diffusion.
By R. Claus. Abstract. A series of calculations are reported for two, subsonic jet in crossflow geometries. The parametric variation examined are the lateral spacing of a row of jets. The first series of calculations corresponds to a widely space jet Author: R. Claus. NUMERICAL CALCULATION OF SUBSONIC JETS IN CROSSFLOW WITH REDUCED NUMERICAL DIFFUSION Russell W.
Claus Natlonal Aeronautlcs and Space Admlnlstratlon LeW1S Research Center Cleveland, OhlO Abstract A serles of calculatlons are reported for two, expenmentally studled, subsonlc Jet In crossflow geometrles.
International Journal for Numerical Methods in Fluids4, 14 Claus, R. Numerical calculation of subsonic jets in crossflow with reduced numerical diffusion.
NASA TM15 McDonnel, V. G., Wood, C. P., and Samuelsen, G. Detailed data set: two component gas and particle velocity statistics in a particle laden jet by: Simplified method of numerical calculation of a three-dimensional turbulent free jet. Authors; “Numerical calculation of subsonic jets in cross flow with reduced numerical diffusion,” AIAA Paper, No.
Kuznetsov, A. Lebedev, A. Sekundov, and I. Smirnova, “Calculation of a turbulent diffusion flame with Author: V. Kozlov. For both of the subsonic and the supersonic conditions, with the increase of the inclination angle, the velocity on the upstream side of the jet exit can be reduced significantly by the strengthened blocking-effect of the cross-flow.
The larger the inclination angle, the more non-uniform the flow at the by: The jet in crossflow, or transverse jet, is a flowfield that has relevance to a wide range of energy and propulsion systems.
Over the years, our group's studies on this canonical flowfield have focused on the dynamics of the vorticity associated with equidensity and variable density jets in crossflow, including the stability characteristics of the jet's upstream shear layer, as a means of Cited by: Three-dimensional compressible jet-in-crossflow calculations using improved viscosity models and adapted grid.
Numerical calculation of Numerical calculation of subsonic jets in crossflow with reduced numerical diffusion book jets in crossflow with reduced numerical diffusion.
These numerical schemes were used in the DNS of subsonic round jet , diffusion jet flame , and supersonic planar jets [12,32], which succeeded in reproducing the statistics in consistent. Numerical modelling of release of subsonic and sonic hydrogen jets. In order to initialise the jet for the AEROPLUME calculation, FRED first calculates the mass flow rate and the conditions at the expanded diameter.
Ethan S. Hecht, David M. ChristopherValidation of a reduced-order jet model for subsonic and under-expanded hydrogen jets Author: Pratap Sathiah, Chris M. Dixon. Sufficient mixing between the supersonic airstream and the injectant is critical for the design of scramjet engines.
The information in the two-dimensional supersonic jet-to-crossflow flow field has been explored numerically and theoretically, and the numerical approach has been validated against the available experimental data in the open by: LiuYang et al.
 used the same numerical calculation method to perform numerical verification on subsonic-supersonic shear mixing flow at normal temperature. The final numerical calculation results are in good agreement with the experimental results, which proved that the numerical calculation method based on OpenFOAM computing platform is File Size: 1MB.
In the present paper, the influence of shock wave position on sonic transverse hydrogen micro-jets in supersonic crossflow is investigated. This study focuses on mixing and shock interaction of the hydrogen jet in a Mach crossflow with various jet conditions. Flow structure and fuel/air mixing mechanism were investigated by: Direct numerical simulation(DNS) of spatially developing round turbulent jet flow with Reynolds number 4, was carried out.
Over 20 million grid points were used in this simulation. Fully compressible three-dimensional Navier–Stokes equations were solved.
High order explicit spatial difference schemes and Runge–Kutta time integration scheme were used to calculate derivatives and Cited by: The gas-liquid interaction process of a liquid jet in supersonic crossflow with a Mach number of was investigated numerically using the Eulerian-Lagrangian method.
In this study, analysis of flow properties around a sphere and its aerodynamic coefficients in the high-Mach-and-low-Reynolds-numbers conditions is carried out by direct numerical simulations solving the three-dimensional compressible Navier–Stokes equations. The calculation is performed on a boundary-fitted coordinate system with a high-order scheme of sufficient by: The model is applied to the configuration of a round jet exhausting perpendicularly through a flat plate into a uniform crossflow for a range of jet-to-crossflow velocity ratios from 3 to It is demonstrated that the model is capable of describing the measured pressure distribution on the flat plate with model parameters that are compatable Cited by: 7.
Large Eddy Simulation of liquid jet primary breakup in supersonic air crossflow. for convenience in numerical calculation, in simulations of single-phase jet in crossflow shown in the. For numerical stability, a minimum level of numerical diffusion or artificial viscosity is to be added to the central discretization of the flux terms [11, 17].
Although the upwind schemes are the natural choices for high-speed flow computations, the central schemes also bear some advantages like algorithmic simplicity and easier Cited by: 5. Abstract. A physical and mathematical model of turbulent combustion of subsonic gas fuel jet flows flowing into an air space is proposed.
The processes are described by averaged equations of the boundary layer with a turbulent viscosity model and a combustion diffusion by: 1. The jet in crossflow, or transverse jet, is a flowfield that has relevance to a wide range of energy and propulsion systems. Over the years, our group's studies on this canonical flowfield Author: Ann Karagozian.
1 DIRECTIVITY ANALYSIS OF SOUND IN TURBULENT EXHAUST JETS WITH LAMINAR CROSS-FLOW: A NUMERICAL STUDY Orddom Y Leav1, Benjamin S Cazzolato1 and Carl Q Howard1 1School of Mechanical Engineering University of Adelaide Australia, Adelaide SAAustralia.
Numerical Computation of Compressible and Viscous is written for those who want to calculate compressible and viscous flow past aerodynamic bodies. As taught by Robert W. MacCormack at Stanford University, it allows readers to get started in programming for solving initial value problems/5(2). Three-Dimensional Viscous Flow Computations of a Circular Jet in Subsonic and Supersonic numerical diffusion with a single jet and a plane of the Chassaing et.
al study examined the subsonic turbulent jets in a cross flow for cylindrical and coaxial jets. Velocity ratios of 2 to 6 were tested. Detailed. velocity measurements were. The Geared Turbofan technology is one of the most promising engine configurations to significantly reduce the specific fuel consumption.
In this architecture, a power epicyclical gearbox is interposed between the fan and the low pressure spool. Thanks to the gearbox, fan and low pressure spool can turn at different speed, leading to higher engine bypass by: 4. Experimental characterization and numerical simulation of a sooting lifted turbulent jet diffusion flame Combustion and Flame, Vol.No.
8 An Experimental and Numerical Study of Heat Transfer From Arrays of Impinging Jets With Surface Ribs. Numerical study of the generation and propagation of entropy noise 2 nd Int.
Conf. on Jets, Wakes and Separated Flows, ICJWSF SeptemberTechnical University of Berlin, Berlin, Germany M. Di Domenico, P. Gerlinger, M. Aigner Chemistry and turbulence effects on the numerical simulation of lifted H2/N2 flames in vitiated coflow.
The Knoller & Benz effect was discovered in the early s, in which the flapping airfoil generates aerodynamic thrust force [1, 2].Birnbaum introduced the reduced frequency k that can characterize the flight efficiency using the linear potential theory, and identified that the vortex shedding in the trailing edge is an important factor.
Garrick conducted research to obtain the thrust and Cited by: 1. Triple-deck and direct numerical simulation analyses of high-speed subsonic flows past a roughness element - Volume - G. Mengaldo, M. Kravtsova, A. Ruban, S. SherwinCited by: 7. Near-Wall Modeling of Turbulent Convective Heat Transport in Film Cooling of Turbine Blades With the Aid of Direct Numerical Simulation Data Djamel Lakehal.
strategy of Lakehal et al. developed for calculating jets in crossflow. of the temperature field be well predicted and the strength of the secondary vortices reduced. Furthermore Cited by: To accelerate convergent of numerical solution of the main equations, suitable boundary conditions could be used.
To do so, the follow equations, are the primary conditions of supersonic-subsonic flow . 1 x, T 1 x, V ( x)T (16)Author: Ali Kargar. The last two years have been great for high performance computing in Baden- W¨ urttemberg and beyond. In Julythe new building for HLRS as well as Stuttgart’s new NEC supercomputer – which is still leading edge in G- many – have been inaugurated.
In these days, the SSC Karlsruhe is?nalizing. One of the most challenging tasks of numerical Ship Hydrodynamics is the calculation of ship stern flows.
The quality assessment of the hull form and the design of the propeller will benefit from such calculations if they have sufficient predictive capability.
The article presents the analysis of the 1D flow of compressible fluid by means of analytical and numerical methods. The results from the solution showed that the calculation of dimensionless velocity for particular flow conditions varies in the area of subsonic flow only a very little, when using both methods.
It was found that the dependence of dimensionless velocity on the relative duration Author: Mária Čarnogurská, Tomáš Brestovič, Miroslav Příhoda, Marián Lázár, Natália Jasminská. The generation of screech tones in an underexpanded jet is investigated by means of compressible large eddy simulation (LES).
A three-dimensional planar geometry is considered with the aim of studying screech radiation in a simple jet configuration, whose physics nevertheless remains similar to that of large-aspect-ratio rectangular jets encountered in experimental by: We introduce new Godunov-type semidiscrete central schemes for hyperbolic systems of conservation laws and Hamilton--Jacobi equations.
The schemes are based on the use of more precise information about the local speeds of propagation and can be viewed as a generalization of the schemes from [A. Kurganov and E. Tadmor, J. Comput. Phys., (), pp.
; A. Kurganov and D. Levy, Cited by: Inlets and Nozzles Key Publications. Abbott, John M.: Computational Study of the Aerodynamic Performance of Subsonic Scarf Inlets. AIAA, AIAA/CEAS Aeroacoustics Conference. JuneAtlanta, Georgia. eISBN: On the interpretation of pressure POD modes in the near field of a subsonic jet in terms of hydrodynamic and acoustic pressures.
Experimental and Numerical Study of Jet Noise Reduction for Supersonic Aircraft Using Variable Folding. For the reacting liquid jet problem, a diffusion flame supported by a one-step chemical reaction within the gaseous boundary layer is solved along the ellipse surface in subsonic crossflow.
Typical flame structures and concentration profiles have been calculated for various locations along the jet cross-section as a function of upstream Mach. A numerical analysis of forced-convection heat transfer from a horizontal stationary circular cylinder dissipating a uniform heat flux in a crossflow of air is conducted by solving the full two-dimensional steady-state Navier-Stokes and energy equations in the range of the Reynolds numbers from to (based on diameter).
principles and consist of convection-diffusion-reactionequations written in integral, differential, or weak form. In particular, we discuss the qualitative properties of exact solutions to model problems of elliptic, hyperbolic, and parabolic type.
Next, we review the basic steps involved in the design of numerical approximations and.American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA where rHg = g cm-3 is the density of mercury and g = m s-2 is the acceleration of gravity. The mean value of h measured at sea level is cm, and the corresponding atmospheric pressure is x kg m-1 s-2 in SI units.
The SI pressure unit is called the Pascal (Pa); 1 Pa = 1 kg m-1 s