Recent Developments of the Navier Stokes Multi Block (NSMB) CFD solver

Hoarau, Yannick; Pena, Dorian; Vos, Jan B.; Charbonier, Dominique; Gehri, Alain; Braza, Marianna; Deloze, Thibaut; Laurendeau, Éric

doi:10.2514/6.2016-2056

Cited by 46 publications

(24 citation statements)

References 94 publications

(87 reference statements)

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“…The time dependent Navier-Stokes equations have been solved under the conservative form in a finite-volume structured grid formulation, using the Navier-Stokes Multi-Block (NSMB) code [15], in both two and three dimensions. The Navier-Stokes equations in 3D Cartesian coordinates, for a viscous perfect gas can be expressed in conservative form as:…”

Section: Numerical Approach and Turbulence Modellingmentioning

confidence: 99%

Morphing of a supercritical wing by means of trailing edge deformation and vibration at high Reynolds numbers: Experimental and numerical investigation

Simiriotis

Jodin

Marouf

et al. 2019

Journal of Fluids and Structures

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This article examines the morphing effects of the trailing-edge deformation and vibration on the turbulent structures in the wake of a supercritical Airbus-320 wing. It is shown that the electroactive morphing has the capacity to produce an enhanced aerodynamic performance (lift increase, drag reduction) and reduce the amplitude of instability modes associated to aerodynamic noise. The appropriate actuation is achieved with piezoactuators placed in the trailing edge region. The work presented has been carried out numerically using the Navier-Stokes Multi Block (NSMB) code, as well as experimentally with measurements obtained in the S4 wind tunnel of IMFT by means of TRPIV (Time-Resolved PIV) with a sampling rate around 10 KHz. The Reynolds number is 1 Million. The study is carried out in the low subsonic regime at an incidence angle of 10 • , corresponding to take-off/landing flight phases and analyses significant morphing effects obtained by optimal deformations and vibrations of the near trailing edge region. The interactions that are prompted in the wake region are analyzed by means of Proper Orthogonal Decomposition (POD), considering the near wake structure in respect of the morphing effects. The effects on the aerodynamic coefficients thanks to manipulation of specific vortex dynamics in the shear layers and the wake are discussed and optimal frequency/amplitude ranges for the vibrations are quantified.

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Section: Numerical Approach and Turbulence Modellingmentioning

confidence: 99%

Morphing of a supercritical wing by means of trailing edge deformation and vibration at high Reynolds numbers: Experimental and numerical investigation

Simiriotis

Jodin

Marouf

et al. 2019

Journal of Fluids and Structures

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“…NSMB is an MPI-parallelized, finite-volume code for structured grids with a wide variety of numerical schemes and it has been extensively tested in studies of hypersonic flows. 38,39 The spatial discretization is based on a 4th-order, central difference scheme, whereas a 4th-order Runge-Kutta method is used for time integration. Artificial numerical dissipation is added to capture the shock and to suppress spurious oscillations.…”

Section: B Direct Numerical Simulationsmentioning

confidence: 99%

Numerical Investigation of Roughness Effects on Transition on Spherical Capsules

Hein

Theiß

Giovanni

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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The state of the boundary layer on space re-entry vehicles significantly affects the design of the thermal protection system. However, the physical mechanism that leads to the laminar-turbulent boundary-layer transition on blunt spherical capsules remains an open question in literature. This work numerically assesses the potential of roughness-induced non-modal disturbance growth on re-entry capsules with a spherical-section forebody by optimal transient-growth theory and direct numerical simulation. Two different sets of wind-tunnel experiments are considered. Optimal transient-growth studies have been performed for the blunt capsule experiments at Mach 5.9 in the Hypersonic Ludwieg tube Braunschweig (HLB) of the Technische Universität Braunschweig. In some of these measurements, the capsule model was equipped with a specifically designed patch of distributed micron-sized surface roughness. The transient-growth results for the HLB capsule are compared to corresponding numerical data for a Mach 6 blunt capsule experiment in the Adjustable Contour Expansion (ACE) facility of the Texas A&M University (TAMU) at lower Reynolds number. Similar trends are observed for both configurations. In particular, a rather low maximum energy gain is noted for the surface temperature conditions of the experiments. It is shown that the surface temperature dependence of the optimal transient-growth results is very similar for both capsule configurations. Moreover, the generation of stationary disturbances by well-defined roughness patches on the capsule surface is studied for the conditions of the HLB experiment using direct numerical simulations (DNS). To help explain the observed laminar-turbulent transition downstream of the roughness patch in some of the HLB capsule experiments, additional simulations were carried out to study the evolution of unsteady perturbations within the steady disturbance flow field due to the roughness patch. However, the DNS did not provide any indication of modal or non-modal disturbance growth in the wake of the roughness patch, and hence, the physical mechanism underlying the observed onset of transition remains unknown.

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“…The ice accretion modules are developed in the NSMB Solver (Navier-Stokes Multi-block solver) [32,12]. The NSMB solver uses structured, multi-block, chimera grids, supports grid motion, contains parallel compressible and incompressible NS solvers and is able to treat embedded grid techniques such as IBM and LS.…”

Section: Numerical Methods and Governing Equationsmentioning

confidence: 99%

Multi-Step Ice Accretion Simulation Using the Level-Set Method

Al-Kebsi¹,

Mosé²,

Hoarau³

2019

SAE Technical Paper Series

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Ice accumulation in aircraft is modelled using the Level-Set (LS) method. Current two-dimensional and threedimensional icing models are limited regarding complex re-meshing due to ice accretion. The Level-Set method allows fully multi-step simulation of ice accretion. The solid boundary is treated implicitly or explicitly. The solid body can be defined via a characteristic level set function in the former case, and as a layer or list of points in the later. Consequently, the boundary conditions for the airflow are applied through a penalization term, or by direct forcing. Correspondingly, the droplet transport is computed using an Eulerian approach in an Immersed Boundary Method (IBM) coupled with Level-Set (IBM-LS) framework, in which the droplet fields impinge on an explicit layer of cells defined by the LS function using a discrete IBM formulation of the interface.

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Recent Developments of the Navier Stokes Multi Block (NSMB) CFD solver

Cited by 46 publications

References 94 publications

Morphing of a supercritical wing by means of trailing edge deformation and vibration at high Reynolds numbers: Experimental and numerical investigation

Morphing of a supercritical wing by means of trailing edge deformation and vibration at high Reynolds numbers: Experimental and numerical investigation

Numerical Investigation of Roughness Effects on Transition on Spherical Capsules

Multi-Step Ice Accretion Simulation Using the Level-Set Method

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