CAA lab :: computations

Supersonic flow over inclined backward-facing step

Unstructured 3D mesh with spanwise periodic BC, 18.5M nodes, hybrid scheme EBR, SST IDDES, synthetic turbulence at inflow, code NOISEtte. Model case: M=3, Re=4.9e6, step angle 45°. Fields shown in mid-span cross-section: numerical Schlieren (density gradient magnitude) (top), vorticity magnitude (bottom).

Flow around helicopter main rotor. Turbulent flow structures

Unstructured 3D mesh with 191M nodes, 990M elements, scheme EBR5, DES+SA, code NOISEtte. Q-criterion isosurfaces colored by vertical flow velocity.

Flow around a wing with high-lift devices. Turbulence and aeroacoustics. Model case 30P30N

Unstructured 3D mesh with spanwise periodic BC, 30M nodes, scheme EBR5, IDDES, code NOISEtte. Model case 30P30N (Pascioni, Kyle & Cattafesta, Louis. (2016). DOI: 10.2514/6.2016-2960) Fields shown in mid-span cross-section: vorticity magnitude (turbulence), pressure time derivative (acoustics), turbulent viscosity (turbulence)

Subsonic immersed unheated round jet

Re=1.1e6 (based on nozzle diameter and jet velocity), M=0.9. The computational setup is provided by M.Kh. Strelets and M.L. Shur from SPbPU. Computed using research code NOISEtte. Approach: hybrid RANS-LES DDES (based on Spalart-Allmaras turbulence model). Numerical scheme: higher accuracy EBR scheme. Mesh size: 8.8M nodes (160 nodes in azimuthal direction). Number of CPU cores: 700 (Lomonosov-2 supercomputer).

Hot underexpanded round jet

Re=1.27e6 (based on nozzle diameter and jet fully expanded velocity), M=2.2. The computational setup is provided by M.Kh. Strelets and M.L. Shur from SPbPU. Computed using research code NOISEtte. Approach: hybrid RANS-LES DDES (based on Spalart-Allmaras turbulence model). Numerical scheme: higher accuracy hybrid WENO-EBR scheme. Mesh size: 4.55M nodes (80 nodes in azimuthal direction). Number of CPU cores: 768 (Sarov supercomputer).

Hot underexpanded round jet: turbulence+acoustics

Transonic turbulent separated flow behind axisymmetric afterbodies

Re=1.2e6 (based on first cylinder diameter and inflow velocity), M=0.7. [Depres and Reijaasse, AIAA J., 2004] Computed using research code NOISEtte. Approach: hybrid RANS-LES DDES (based on Spalart-Allmaras turbulence model). Numerical scheme: higher accuracy EBR scheme. Mesh size: 8.1M nodes (120 nodes over azimuthal direction).

Turbulent transonic flow over wedge with back facing step

Re=7.2e6 (based on the length of plate upstream back step leading edge and inflow velocity), M=0.913. Computed using research code NOISEtte. Approach: hybrid RANS-LES IDDES (based on Spalart-Allmaras turbulence model). Numerical scheme: higher accuracy EBR scheme. Mesh size: 26M nodes.

Turbulent flow over M219 cavity

Re=1.37e6 (based on cavity depth and inflow velocity), M=0.85. [de Henshaw, QinetiQ, 2002] Computed using research code NOISEtte. Approach: hybrid RANS-LES IDDES (based on Spalart-Allmaras turbulence model). Numerical scheme: higher accuracy EBR scheme. Mesh size: 4M nodes.

DNS round jet & cylinder

Re=14000, Mach=0.3, non-structured mesh of 10000000 nodes, high-order vertex-centered scheme. This DNS has been performed in KIAM RAS by A. Gorobets, I. Abalakin and T. Kozubskaya on Lomonosov supercomputer of MSU using 1024 CPU cores, 2010.

2D supersonic flow around a cylinder in a channel

Navier--Stokes equations. Mach=3.5, Re=10000. Unstructured 2D quad mesh with 350K nodes. Scheme EBR-WENO. Top: specific volume; bottom: pressure. Setup: Chaudhuri et al., JCP 230(2011) 1731--1748; White et al. AIAA paper 2012-4263. Code: NOISEtte

Численное моделирование обтекания эллиптического цилиндра с двумя степенями свободы (M=0.1, Re=100)

Колебание эллиптического цилиндра под действием индуцированных аэродинамических сил. Расчет на двухмерной неструктурированной сетке с использованием метода погруженных границ. Программный комплекс NOISEtte. Показано поле модуля вектора завихренности.

Simulation of aeroacoustic problems using scale-resolving approaches