An Overview of the NPARC Alliance's Wind-US Flow Solver

Nelson, Chris

doi:10.2514/6.2010-27

Cited by 28 publications

(17 citation statements)

References 112 publications

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“…The current practical state-of-the-art in RANS-based techniques is emphasized, utilizing some of our own recent experiences. Our efforts utilized the Wind-US code [12][13][14] which is a production RANS solver with several available turbulence models. Discussion of more computationally intensive techniques such as LES, including hybrid RANS-LES approaches, will be provided.…”

Section: Introductionmentioning

confidence: 99%

Status of turbulence modeling for hypersonic propulsion flowpaths

Georgiadis

Yoder

Vyas

et al. 2014

Theor. Comput. Fluid Dyn.

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Section: Introductionmentioning

confidence: 99%

Status of turbulence modeling for hypersonic propulsion flowpaths

Georgiadis

Yoder

Vyas

et al. 2014

Theor. Comput. Fluid Dyn.

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“…An Eulerian solution for the chemically-reacting, ionized, turbulent plume is produced using the Wind-US flow solver [2], which is provided by the NPARC Alliance, a partnership of NASA Glenn Research Center, Air Force Arnold Engineering and Development Center, and Boeing. Wind-US is well-validated for reacting and turbulent flows.…”

Section: A Wind-us Plume Modelmentioning

confidence: 99%

Numerical Prediction of the Electric Field Produced Within Launch Vehicle Plumes

Engblom¹,

Perrell²,

Coutu³

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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A novel Eulerian-Lagrangian numerical scheme is developed to characterize the electric nature of rocket plumes. An Eulerian flow solver (Wind-US) is used to simulate the ionized, chemical non-equilibrium, turbulent plume produced by a methane-oxygen rocket engine, including a detailed chemi-ion reaction set (34-species, 178-reactions).A one-way Lagrangian solver is described for simulation of soot effects on the electrical nature of the plume using the Eulerian flow solution, and addresses ion emission from soot, and soot-ion attachment. The numerical scheme is demonstrated for a hypothetical 15000-lbf thrust rocket methane-oxygen engine. The sensitivity of the electric nature of the plume is evaluated for a stoichiomtetric and fuel-rich mixture. Results from initial demonstrations of this scheme suggest that substantial ion fields are generated witin the plumes, and that soot particles capture the free electrons to form a region of negatively charged particles which likely persist for hundreds of nozzle exit diameters downstream. Nomenclature C D= drag coefficient m = mass of soot particle r = radial distance from centerline S = surface area of soot particle u rel = relative velocity -gas velocity minus soot particle velocity ∆t = time step x = axial distance from nozzle throat φ = equivalence ratio (also ER) ρ = density of gas

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“…These include REACTMB [7,8], WIND-US [9,10], TAU-code [11], VULCAN [12,13] and the recent SU2 [14,15]. OpenFOAM [16] is a well-established open platform in the scientific community.…”

Section: Introductionmentioning

confidence: 99%

Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

Hoste

Casseau

Fossati

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

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Two open-source solvers, Eilmer and hyFoam, are here considered for their performance in simulating high-speed flows in different flow conditions and geometric configurations typical of propulsive systems at supersonic speeds. The goal is to identify the open-source platform providing the best compromise between accuracy, flexibility and computational cost to eventually simulate the flow fields inside ramjet and scramjet engines. The differences in terms of discretization and solution methods of the selected solvers are discussed in terms of their impact on solution accuracy and computational efficiency and in view of the aerothermodynamic analysis and design of future transatmospheric propulsive systems. In this work steady state problems are considered. Numerical results of two scramjet type engines demonstrated a similar predictive capability of both codes in non-reacting conditions. These results highlight their potential to be considered for further characterization of overall engine performance. * PhD Candidate, AIAA Student Member. † Lecturer, AIAA Member . ‡ Senior Lecturer.

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An Overview of the NPARC Alliance's Wind-US Flow Solver

Cited by 28 publications

References 112 publications

Status of turbulence modeling for hypersonic propulsion flowpaths

Status of turbulence modeling for hypersonic propulsion flowpaths

Numerical Prediction of the Electric Field Produced Within Launch Vehicle Plumes

Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

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