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Aeroacoustique

Description : Shock-cell noise obtained with a Large Eddy aeroacoustic Simulation from a single stream jet. The jet is cold supersonic and under-expanded with a perfectly expanded Mach number of M = 1.15 and Re_s = 1.00 E+6.

 

Description : Shock-cell noise obtained with a Large Eddy aeroacoustic Simulation from a dual stream jet. The primary stream is cold and subsonic with an exit Mach number of M_p = 0.89 and a Reynolds number of Re_p = 0.57 E+6. The secondary stream is cold supersonic and under-expanded with a perfectly expanded Mach number of M_s = 1.20 and Re_s = 1.66 E+6. The computations are performed with the structured multi-block solver elsA.

 

Description : « Simulation of shock-cell noise for a double-flux exhaust with elsA Solver, 2014 – AeroTraNet-2 »