SU2-NEMO: An Open-Source Framework for High-Mach Nonequilibrium Multi-Species Flows

Maier, W; Needels, Jacob T.; Garbacz, Catarina; Morgado, Fábio; Alonso, Juan J.; Fossati, Marco

doi:10.3390/aerospace8070193

Cited by 27 publications

(4 citation statements)

References 40 publications

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“…The test cases were simulated with the SU2-NEMO [12] solver to assess the effect of grid element type and orientation on the solution obtained with anisotropic unstructured grids (2D and 3D cases) and fully structured grids (2D cases only). First, a single isolated two-dimensional cylinder and three-dimensional sphere are analysed and results are compared with the available reference data in literature.…”

Section: Numerical Resultsmentioning

confidence: 99%

“…In the past few years, new numerical methods, tools and solvers have been gradually incorporated into the SU2 infrastructure. The requirement of simulating chemically-reactive multi-species and non-equilibrium flows led to the development of the SU2-NEMO (Non-Equilibrium MOdels) solver [11,12]. The thermochemistry models used in SU2-NEMO are provided through coupling of the solver with the Mutation++ library [13].…”

Section: The Open-source Solver Su2-nemomentioning

confidence: 99%

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Impact of Anisotropic Mesh Adaptation on the Aerothermodynamics of Atmospheric Reentry

2022

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The presence of complex geometries and/or multiple bodies during atmospheric re-entry may lead to complex and directional flow features such as shock waves and shear layers that need to be correctly predicted to ensure accurate calculation of the aerothermal loads during re-entry. Central in ensuring reliable numerical prediction of loads is the adoption of meshes that ensure grid independence and minimize the misalignment between the directional flow features and the grid cells interfaces, a situation that is known to give rise to nonphysical behaviours and spurious oscillations. The use of anisotropic unstructured grid adaptation is here presented as a means to ensure appropriate grid resolution and alignment with directional flow features for cases where the use of structured grids is not always possible or practical. Results highlight the effectiveness and reliability of anisotropic mesh adaptation in successfully predicting the location of shock discontinuities as well as surface aerothermodynamic quantities while providing results comparable with established approaches relying on structured meshes. Results are presented for single and multiple bodies cases through comparison with experimental data and reference numerical solutions.

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Section: Numerical Resultsmentioning

confidence: 99%

Section: The Open-source Solver Su2-nemomentioning

confidence: 99%

Impact of Anisotropic Mesh Adaptation on the Aerothermodynamics of Atmospheric Reentry

2022

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“…It is shown in [21][22][23][24] that all turbulent scales can be modeled with moderate computational cost and the capability to predict high-temperature/real gas effects with Reynolds Averaged Navier Stokes solvers (RANS). This work uses the SU2-NEMO (NonEquilibrium MOdels) code to RANS fidelity [25][26][27]. To model continuum hypersonic flows, SU2-NEMO solves the Navier-Stokes equations for multi-species gases in thermochemical nonequilibrium.…”

Section: Computational Modeling Of Sfrjmentioning

confidence: 99%

Adaptive Combustion Regulation in Solid Fuel Ramjet

Oveissi,

Goel,

Tumuklu

et al. 2024

AIAA SCITECH 2024 Forum

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Control of the combustion process under hypersonic conditions remains a challenging problem. In this paper, we investigate the application of a data-driven, learning-based control technique to regulate a combustion process evolving inside a solid fuel ramjet to regulate the generated thrust under unknown operating conditions. A computational model to simulate the combustion dynamics is developed by combining compressible flow theory with equilibrium chemistry. The computational model is simulated to ascertain the combustion dynamics' stability and establish the engine's operational envelope. Based on retrospective cost optimization, an online learning controller is then integrated with the computational model to regulate the generated thrust. Numerical simulation results are presented to demonstrate the robustness of the adaptive control system.

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“…The unsteady, dimensionless, axisymmetric, compressible Navier-Stokes equation was employed for the viscous case. For multi-species air in thermochemical non-equilibrium state [22][23][24], this Navier-Stokes equation can be expressed in the vector equation [25] as:…”

Section: Governing Equationsmentioning

confidence: 99%

High Enthalpy Non-Equilibrium Expansion Effects in Turbulent Flow of the Conical Nozzle

et al. 2023

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High enthalpy stagnation gas can be converted into hypervelocity flow through the contraction—expansion nozzle. The enthalpy flow in the nozzle can be divided into three regions: an equilibrium region, a non-equilibrium region, and a frozen region. The stagnation gas with a total enthalpy of 13.4 MJ/kg is used to analyze the thermochemical non-equilibrium effects. At the selected conditions, the effects of a conical nozzle under different expansion angles of the expansion section, curvature radius of the throat, throat radius, and convergence angle of the convergent section are investigated. Based on the Spalart–Allmaras one-equation turbulence model with the Catris–Aupiox compressibility correction, a multi-block solver for axisymmetric compressible Navier–Stokes equations is applied to simulate the thermochemical non-equilibrium flow in several high enthalpy conical nozzles. The multi-species two-temperature equation is employed in the calculation. The results reveal three interesting characteristics: Firstly, the thermochemical non-equilibrium effects are sensitive to the maximum expansion angle and throat radius but not to the radius of throat curvature and contraction angle. Secondly, as the maximum expansion angle decreases and the throat radius increases, the flow approaches equilibrium state. When the maximum expansion angle decreases from 12° to 4°, the freezing temperature decreases from 2623 K to 2018 K. When the throat diameter increased from 10 mm to 30 mm, the freezing temperature decreased from 2442 K to 2140 K. Finally, the maximum expansion angle and throat radius not only affect the position of the freezing point but also the flow field parameters, such as temperature, Mach number, and species mass fraction.

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SU2-NEMO: An Open-Source Framework for High-Mach Nonequilibrium Multi-Species Flows

Cited by 27 publications

References 40 publications

Impact of Anisotropic Mesh Adaptation on the Aerothermodynamics of Atmospheric Reentry

Impact of Anisotropic Mesh Adaptation on the Aerothermodynamics of Atmospheric Reentry

Adaptive Combustion Regulation in Solid Fuel Ramjet

High Enthalpy Non-Equilibrium Expansion Effects in Turbulent Flow of the Conical Nozzle

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