Overview on Turbulence & Aeroacoustics activities

• providing reliable predictions -- direct computation of aerodynamic noise -- by highly accurate numerical simulations
• understanding of noise generation mechanisms
• giving insight for flow control and noise reduction

Examples of Direct Noise Computation & Experimental Results

• Large eddy simulation of an overexpanded supersonic jet
• Underexpanded supersonic jet & broadband shock noise
• Shock-vortex interactions
• Aeroacoustics phenomena in subsonic and transonic ducted flows
• Screech tones in an underexpanded rectangular supersonic jet
• Subsonic jet noise
• Noise generated by a mixing layer
• Acoustic radiation of instability waves
• Noise radiated by a flow over a cavity

    and contributions at efluids

• eFluids - Gallery of Flow Images, supersonic jet noise
• eFluids - Gallery of Flow Images, high-Reynolds-number susbonic jet noise

Current projects

• ANR JESSICA

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Large eddy simulation of an overexpanded supersonic jet

Large eddy simulation of an overexpanded supersonic jet   Snapshot of density gradient norm in gray scale, azimuthal vorticity in color scale in the jet, and fluctuating pressure in color scale outside the jet. Pressure levels from -8000 to 8000 Pa (color bar from -5000 to 5000 Pa).   Reynolds number of 10^5, exit Mach number of 3.30, static pressure and temperature of 0.5x10^5~Pa and of 360~K.   Ph.D. Thesis of Nicolas de Cacqueray, in collaboration with the CNES

Click on the picture to enlarge !

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Underexpanded supersonic jet & broadband shock noise

Schlieren photography of a round supersonic jet at Mach number 1.5   Convergent nozzle - Md=1 - Mj=1.55 - NPR=4. Lower part, mean flow field obtained by averaging 1000 pictures   Benoît André & Thomas Castelain

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Shock-vortex interactions

Superposition of density gradient (gray scale), and of pressure (color scale). Shock Mach number of 1.2 and maximum vortex Mach number of 0.25. Bogey, de Cacqueray & Bailly (2009, JCP)

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Aeroacoustics phenomena in subsonic and transonic ducted flows

Strong interactions between shock oscillations, internal aerodynamic noise and acoustic duct modes are often observed in confined flows but are undesirable to prevent vibrations and fatigue of structures. In order to compute this kind of phenomena, a numerical solver called SAFARI (Simulation of Aeroacoustics in Fluids And Resonances and Interactions, EDF) has been developed. Compressible Navier-Stokes equations are solved using high-order finite difference schemes. A non-linear adaptive filter is implemented to capture strong shock waves and a high-order overset grid ability is introduced in order to treat complex geometries. These numerical techniques allow to carry out direct simulation of aeroacoustic couplings in subsonic and transonic flows. A transonic flow passing a sudden expansion in a duct is studied. For certain values of the pressure ratios tau (tau = Poutlet/Pinlet), the supersonic expansion ends up after a normal shock. Strong coupling between the self-sustained oscillations of the normal shock and the longitudinal acoustic modes is captured as in the experiments. An instantaneous snapshot of the density gradient modulus is represented in a plane perpendicular to the spanwise direction. Others flow regimes have been studied. For lower pressure ratios, the flow is entirely supersonic with oblique shocks. For higher pressure ratios, the flow is asymmetric and exhibits shock cells.   Emmert et al., Phys. Fluids, 2009

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Generation of screech tones in an underexpanded supersonic jet

Snapshot of the density modulus, of the spanwise vorticity and of the near-field pressure, in a plane perpendicular to the spanwise direction. The nozzle lips are represented in black. (fully expanded jet Mach number 1.55, Reynolds number 60,000) Compression shocks corresponding to high-density gradients are observed inside the jet plume. Upstream-propagating wave-fronts associated with screech tones radiation are also clearly visible on either side of the jet. A further study of the simulation data have permitted to provide evidences of the connection between the shock-leakage process (Suzuki & Lele, JFM, 2003) and the generation of screech tones. Berland et al., Phys. Fluids, 2007

 

The jet operates at off-design conditions with a Mach number M = 1.55. The Reynolds number is Re = 100000. A snapshot of instantaneous spanwise vorticity is shown in purple and green, and corresponding isosurfaces of pressure are in yellow. Upstream-propagating wavefronts, corresponding to screech tones, are visible on both sides of the jet. DFG - CNRS project with T.U. Munich - Pr. Friedrich.

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Direct Noise Computation of subsonic jet

Influence of the Reynolds number on the turbulent development of transitional, isothermal subsonic round jets and on their radiated noise. The Mach number of the jets is 0.9, and their Reynolds numbers are: (a) 1,700; (b) 2,500; (c) 5,000 and (d) 400,000. The flow and the acoustic fields are calculated directly using compressible Large Eddy Simulations. The vorticity norm is represented in the jet flow, and the fluctuating pressure is visualized outside.   Bogey & Bailly, 2006, Theoret. Comput. Fluid Dyn.

Calcul direct du bruit d'un jet rond par simulation compressible des grandes échelles (LES)   Nombre de Mach M = 0.9 Nombre de Reynolds ReD = 4 x 105   Bogey et al., 2002, Computer & Fluids

Calcul direct du bruit d'un jet subsonique circulaire par simulation compressible des grandes échelles. Représentation d'une composante de la vorticité dans l'écoulement, et du champ acoustique à l'extérieur.   Nombre de Mach M = 0.9 Nombre de Reynolds ReD = 6.5 x 104   Bogey et al., 2003, Theoret. Comput. Fluid Dyn.

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Calcul direct du bruit d'une couche de mélange par simulation compressible des grandes échelles. Représentation d'une composante de la vorticité dans l'écoulement, et du champ acoustique à l'extérieur.   Mc = 0.18    Re = 12800   Bogey et al., 2000, AIAA Journal.

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Calcul direct du rayonnement acoustique d'ondes d'instabilité dans un jet plan.   M = 2   Proceedings of the 3rd CAA workshop, 2000.

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Calcul direct du bruit d'un écoulement affleurant une cavité. Représentation du gradient transversal de la masse volumique obtenu par DNS à gauche, et expérience de Karamcheti (NACA 3847, 1955) à droite.   M = 0.7   Gloerfelt et al., 2003, J. Sound Vib.

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