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3 edition of A two-dimensional numerical simulation of a supersonic, chemically reacting mixing layer found in the catalog.

A two-dimensional numerical simulation of a supersonic, chemically reacting mixing layer

J. Philip Drummond

A two-dimensional numerical simulation of a supersonic, chemically reacting mixing layer

by J. Philip Drummond

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  • 8 Currently reading

Published by National Aeronautics and Space Administration, Scientific and Technical Information Division, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Fluid mechanics.

  • Edition Notes

    Other titlesTwo dimensional numerical simulation of a supersonic, chemically reacting mixing layer
    StatementJ. Philip Drummond.
    SeriesNASA technical memorandum -- 4055
    ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Division.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17095800M

    This numerical study was conducted to investigate the flow properties in a model scramjet configuration of the experiment in the T4 shock tunnel. In most numerical simulations of flows in shock tunnels, the inflow conditions in the test section are determined by assuming the thermal equilibrium of the gas. To define the inflow conditions in the test section, the numerical Author: Seoeum Han, Sangyoon Lee, Bok Jik Lee.   Numerical Analysis of Two-Dimensional Turbulent Super-Cavitating Flow around a Cavitator Geometry. Numerical Simulation of Supersonic Chemically Reacting Turbulent Jets. Alexander Molchanov; Stress Limiter Consideration for k-omega Turbulence Models in Shock-Wave/Turbulent Boundary-Layer Interactions in Supersonic and Hypersonic Flows.

    page 1 two-dimensional modeling of a chemically reacting, boundary layer flow in a catalytic reactor by patrick d. griffin a thesis presented to the graduate school of the university of flor ida in partial fulfillment of the requirements for the degree of master of science university of florida Computational fluid dynamics (CFD) is a branch of fluid mechanics that uses numerical analysis and data structures to analyze and solve problems that involve fluid ers are used to perform the calculations required to simulate the free-stream flow of the fluid, and the interaction of the fluid (liquids and gases) with surfaces defined by boundary conditions.

    Numerical simulation of steady shock and detonation wave configurations in a supersonic chemically reacting flow. Pages Two-dimensional numerical modelling of overtaking shock-wave/moving-body interactions. Time series evaluation of 2-D air and hydrogen supersonic mixing layer by using catalytic reaction. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA


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A two-dimensional numerical simulation of a supersonic, chemically reacting mixing layer by J. Philip Drummond Download PDF EPUB FB2

Towards a Numerical Simulation of Supersonic Mixing & Combustion: Development & Validation of a Computational Solver for Two-Dimensional Compressible Chemically-Reacting Turbulent Flows [Kamel, Mohammed, Owis, Farouk, Idres, Moumen] on *FREE* shipping on qualifying offers.

Towards a Numerical Simulation of Supersonic Mixing & Combustion: Development & Author: Mohammed Kamel, Farouk Owis, Moumen Idres. In this paper, the supersonic chemically reacting mixing layer is simulated with the third order ENN scheme, based on the Navier-Stokes equations, containing transport equations of all species.

The numerical results show that the thickness of mixing layer increases gradually along the flow direction, and that the Kelvin-Helmholtz instabilities may not exist in mixing layer Cited by: 3.

A Two-Dimensional Numerical Simulation of a Supersonic, Chemically Reacting Mixing Layer j. Philip Drummond Langley Research Center Hampton, Virginia National Aeronautics and Space Administration Scientific and Technical Information Division Get this from a library.

A two-dimensional numerical simulation of a supersonic, chemically reacting mixing layer. [J Philip Drummond; United States. National Aeronautics and Space Administration.

Scientific and Technical Information Division.]. The hypervelocity two-dimensional reacting supersonic mixing layer experiments of Erdos et al. with a H 2 /air stream have been simulated with model free fine grid calculations on. Towards a Numerical Simulation of Supersonic Mixing & Combustion: Development & Validation of a Computational Solver for Two-Dimensional Compressible Chemically-Reacting Turbulent Flows The design Author: Mohammed Kamel.

The hypervelocity two-dimensional reacting supersonic mixing layer experiments of Erdos et al. with a H 2 /air stream have been simulated with model free fine grid calculations on a N–S solver with full and single step chemistry.

Response of the flow to fluctuations in the in-flow stream is utilized to examine chemistry fluid flow interactions. A favourable comparison of the Cited by: A supersonic, spatially developing and reacting mixing layer serves as an excellent physical model for the mixing and reaction processes that take place in a scramjet combustor, This paper describes a study of fuel-air mixing and reaction in a supersonic mixing layer and discusses several techniques that were applied for enhancing the mixing Cited by: This paper proposes a two-dimensional particle method for a plane mixing layer with a single-step and irreversible chemical reaction.

The vorticity an Cited by: 3. A numerical model for mixing layers In the current work, a numerical model has been developed for describing a general two-dimensional, high subsonic or supersonic, chemically reacting flow, and the model has been applied to a two-dimensional supersonic reacting mixing by: The direct numerical simulation (DNS) of two-dimensional compressible turbulent mixing layers is reported in this paper for convective Mach numbers M c =and All scales of flow are resolved with a 2 grid, although results are also obtained for 64 2, 96 2 and 2 grids for the purpose of determining the effective accuracy and grid-independence of our by: 8.

A theoretical and computational study of a laminar, two-dimensional, compressible, mixing, reacting layer with a pressure gradient that accelerates the flow in the direction of the primary stream is performed. One objective is to analyze the problems of a new technology related to combustion occurring in an accelerating transonic flow.

Potential exists for reduction in nitric Cited by: “Effect of ratio of wall boundary-layer thickness to jet diameter on mixing of a normal hydrogen jet in a supersonic stream,” NASA TM X McClinton, C. “Hypersonic technology Past, present and future,” inaugural presentation at the Institute for Future Space Transport, University of by: 4.

Free mixing layers have been extensively studied over the past decades. Direct numerical simulation (DNS) is a reliable tool and has been successfully used for compressibility effects in the turbulent shear layer [1], spatial mixing layers [2], single-phase and two-phase flows [3].

The particle dispersions in the mixing layers for the different. The numerical study of the two-dimensional supersonic hydrogen-air mixing in the free shear layer is performed.

The system of the Favre-Averaged Navier-Stokes equations for multispecies flow is solved using the ENO scheme of the third order accuracy.

The k-ε two-equation turbulence models with compressibility correction are applied to calculate the eddy viscosity : Altyn Makasheva, Altynshash Naimanova, Yerzhan Belyayev. supersonic turbulent flows. The objective of the present paper is to study high speed turbulent gas-particle mixture layer.

Eulerian approach is used for the numerical simulation of supersonic mixing layer of multi-species gas with 2D-DNS. The dispersion of particles is studied following their trajectories in the mixture layer.

Numerical simulation has been widely employed to investigate the compressible flows since it is difficult to carry out the experimental measurements, especially in the reactive flows.

The shock-wave capturing scheme will be necessary for resolving the compressible flows, and moreover the careful treatments of chemical reaction should be considered for proceeding numerical Cited by: 1.

Guirguis et al. [1] performed two-dimensional time-dependent numerical simulation of the convective mixing of two supersonic parallel streams of air.

They simulated a supersonic shear layer in a two dimensional channel of 20 cm long and cm high and used flux corrected transport algorithm neglecting all diffusion transport processes. The two-dimensional Navier-Stokes and species continuity equations are used to investigate supersonic chemically reacting flow problems which are related to scramjet-engine configurations.

A global two-step finite-rate chemistry model is employed to represent the hydrogen-air combustion in the flow. A numerical study on the physics of mixing in two-dimensional supersonic stream Mohammad Alia, and eventually to find out the means of increasing the mixing efficiency.

The two-dimensional full numerical simulation the grid points are clustered nearCited by: 3. TWO-DIMENSIONAL, SUPERSONIC MIXING OF HYDROGEN AND AIR NEAR A WALL Charlie L.

Yates Applied Physics Laboratory, The Johns Hopkins University Silver Spring, Maryland A fuel injection scheme for air-breathing engines employing super- sonic combustion that is particularly attractive at hypersonic flight speeds.Table 1: Description of the numerical tools and their relative computational cost per iteration 4 The temporal mixing layer Background The e ect of a non-uniform density eld over a shear layer has been already studied for a temporal layer [5] and for a spatially developing layer [3,4].

The main features that come out of thoseCited by: 7.A new numerical method is presented here that allows to consider chemically reacting gases during the direct numerical simulation of a hypersonic fluid flow.

The method comprises the direct coupling of a solver for the fluid mechanical model and a Cited by: 8.