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Monday, May 4, 2020 | History

3 edition of Navier-Stokes simulation of the supersonic combustion flowfield in a ram accelerator found in the catalog.

Navier-Stokes simulation of the supersonic combustion flowfield in a ram accelerator

Navier-Stokes simulation of the supersonic combustion flowfield in a ram accelerator

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

    Subjects:
  • Detonation waves.,
  • Navier-Stokes equations.

  • Edition Notes

    StatementShaye Yungster.
    SeriesNASA technical memorandum -- 104439., ICOMP -- 91-10., ICOMP -- no. 91-10.
    ContributionsUnited States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL18035295M

    Supersonic combustion Large-eddy simulation. abstract. This work presents results from large-eddy/Reynolds-averaged Navier–Stokes (LES/RANS) simulations of the well-known Burrows–Kurkov supersonic reacting wall-jet experiment. Generally good agreement with experimental mole fraction, stagnation temperature, and Pitot pressure profiles is. The study presents an improved numerical method to solve the Navier-stokes equations for a flow over a rearward facing step. The validity of these results is confirmed by established experimental data. For example, as it can be seen in Figures 2 and 6 several characteristics of the flow field, namely, in the expansion-corner, in the free.

    Unified Navier-Stokes Flowfield and Performance Analysis of Liquid Rocket Engines Ten-See Wang* NASA Marshall Space Flight Center, Huntsville, Alabama and Yen-Sen Ghent Engineering Sciences, Inc., Huntsville, Alabama In an effort to improve the current composite solutions in the design and analysis of liquid propulsive engines. Navier-Stokes & Flow Simulation CSCI Advanced Computer Graphics Cutler Last Time? CSCI Advanced Computer Graphics Cutler Today • Flow Simulations in Computer Graphics – water, smoke, viscous fluids • Navier-Stokes Equations • Fluid Representations • Basic Algorithm • Data Representation CSCI Advanced Computer Graphics.

    Computational Analysis of Hypersonic Combustion Using Flame Stabilizing Fig. 2: Meshing. Boundary Condition Before the simulation Grid independence test is carried out in order to check the quality of mesh and to get the optimised number of nodes and element of mesh beyond that no further variation in solution is Size: KB. thin-layer Navier-Stokes equations are solved in a time-accu-rate manner to obtain the unsteady flowfield associated with this configuration. The numerically obtained results are com-pared with the experimental results of Ref. 6. A good com-parison of theory and experiment is obtained in the case of time-averaged pressures on the rotor and Size: 2MB.


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Navier-Stokes simulation of the supersonic combustion flowfield in a ram accelerator Download PDF EPUB FB2

Navier-Stokes Simulation of the Supersonic Combustion Flowfield in a Ram Accelerator Shaye Yungster` Institute for Computational Mechanics in Propulsion NASA Lewis Research Center, Cleveland, OH Abstract A computational study of the ram accelerator, a ramjet-in-tube device for accelerating projectiles to ultra-high velocities, is presented.

Get this from a library. Navier-Stokes simulation of the supersonic combustion flowfield in a ram accelerator. [Shaye Yungster; United States. National Aeronautics and Space Administration.]. Potential applications of the ram accelerator include hypervelocity impact studies, hypersonic propulsion research, kinetic energy weapons, and direct launch of acceleration-insensitive payloads to low Earth orbit.

This paper presents an overview of the technology of the ram accelerator and its history and state-of-the-art in the United : Adam P. Bruckner, Carl Knowlen. NUMERICAL SIMULATION OF SUPERSONIC FLOWFIELD WIT H SECONDARY INJECTION flowfield.

In our study, both the freestream and injection are air. When discussing total pressure ratio, the total temperatures of the freestream and injection and the total pressure of the freestream are fixed. The slot width is 1mm, and the Mach number of injection is 1. The. Twenty-Fifth Symposium (International) on CombustiotCl'he Combustion Institute, /pp.

NAVIER-STOKES NUMERICAL SIMULATION OF SUPERSONIC HYDROGEN-FLUORINE COMBUSTION IN CW CHEMICAL LASERS M. ROTINIAN,M. SHUR** AND M. STRELETS+ Chemical Gas Dynamics Laboratory Federal Russian Scientific Center "Applied Chemistry" 14 Cited by: 1. @article{osti_, title = {Navier--Stokes solutions of the flowfield in an internal combustion engine}, author = {Griffin, M D and Anderson, Jr, J D and Diwakar, R}, abstractNote = {The flowfield inside the cylinder of a reciprocating internal combustion engine is calculated by solving the complete Navier--Stokes equations by use of a time-dependent finite-difference technique.

This paper reports on Large Eddy Simulation (LES) of supersonic combustion in a model scramjet combustor based on an Open Source Field Operation. the application of large-eddy simulation methods and related techniques for scramjet combustion calculations.

Some prior work in applying large-eddy simulation methods to supersonic combustion problems has been reported in Genin, et al. [2,3] and Berglund and Fureby [4], who simulated hydrogen-air combustion behind a wedge-shaped.

Yungster S () Navier-Stokes simulation of the supersonic combustion flowfield in a ram accelerator. AIAA paper Google Scholar Yungster S, Eberhardt S and Bruckner AP () Numerical simulation of hypervelocity projectiles in detonable by: Computational fluid dynamics solutions of the full Navier-Stokes equations have been used to numerically simulate the reacting in-bore flowfield for the.

Reynolds-Averaged Navier Stokes Simulation of Scramjet Inlet Flowfield Krishnendu Sinha ∗and Vadivelan C † Abstract The forebody of a hypersonic vehicle based on scramjet propulsion acts as an external compression inlet for the engine.

A typical configuration co nsists of compression ramps and wedges. showing the supersonic jet of vitiated air and the laser beams of the CARS-Rayleigh system.

The facility consists of a water-cooled combustion chamber (burner), a silicon carbide nozzle (sonic convergent, or supersonic convergent-divergent for M= and M=2), with an exit diameter of 10 mm and a coflow Size: 7MB.

Numerical Simulation of Supersonic & Turbulent Combustion with Transverse Sonic Fuel Injection 3 In supersonic combustion, the order of magnitude of characteristic time of the chemical reactions is much less than that of flow residence time.

There-fore, sti↵ness of the source terms arises from the great gap between the time scales of the coupled. Averaged Navier-Stokes/Large Eddy Simulation of supersonic combustion with a strut flame holder using flamelet and unsteady flamelet/progress variable models, in preparation.

(Chapter 5) W. Luo, M. Pourkashanian, D.B. Ingham, L. Ma, Z. Fan, Characteristics of a supersonic flame and flameholding mechanisms in a cavity-based.

The combustion efficiency in supersonic combustion ramjets (scramjets) is strongly dependent on the fuel injection process. This paper investigates the transverse injection of hydrogen into a hypersonic air crossflow at Mach 6. The flow physics are investigated using both Reynolds-averaged Navier-StokesFile Size: 1MB.

A new upwind, parabolized Navier-Stokes (PNS) code has been developed to compute the three-dimensional (3D) chemically reacting flow in scramjet (supersonic combustion ramjet) engines. The code is a modification of the 3D upwind PNS (UPS) airflow code which has been extended in the present study to permit internal flow calculations with.

This chapter describes the development of a general three-dimensional multiple grid zone Navier-Stokes flowfield simulation program (ENS3D-MPP) designed for efficient execution on the Intel Paragon massively parallel processor (MPP) supercomputer, and the subsequent application of this method to the prediction of steady viscous flowflelds about complete modern fighter Cited by: 1.

The University of Virginia’s Supersonic Combustion Facility (SCF) (see Figure 1) is a small-scale direct-connect ram/scramjet combustor apparatus whose operation is designed to simulate flight conditions at Mach 5 enthalpy. [1] It is vertically mounted and consists of an inlet nozzle, constant-area isolator, combustor, and extender.

The simulation of high-speed flow involves unique challenges such as the treatment of strong flow gradients associated with shock waves and expansion fans, as well as the modeling, at hypersonic speeds, of air chemistry effects.

However, supersonic flow also produces the effect of limited zones of influence, which allows for single-sweep flow solution processes. The. Navier-Stokes codes applied to a Supersonic Retro-Propulsion (SRP) wind tunnel test.1 2 Advancement of SRP as a technology hinges partially on the ability of computational SRP is envisioned as a replacement for supersonic methods to accurately predict vehicle aerodynamics during the SRP phase of atmospheric descent.

A comparison of chemical propulsion, nuclear thermal propulsion, andmultimegawatt electric propulsion for Mars missions ROBERT FRISBEE, JOHN BLANDINO and.Navier-Stokes/Euler with Slip The new theory of flight is evidenced by the fact that the incompressible Navier-Stokes equations with slip boundary conditions are computable using less than a million mesh points without resolving thin boundary layers in DFS as Direct Finite Element Simulation, and that the computations agree with experiments.• The solutions obtained from numerical simulation performed with FEM tool is in good agreement with shock-expansion theory.

• The difference in the values of coefficients obtained from SE-theory and compressible NS numerical simulation indicates the .