Abstract
A three-dimensional computational aeroacoustic procedure is developed to simulate the screech phenomenon from a supersonic circular jet. The 3D Navier-Stokes equations and a modied two equations standard k turbulence model are solved in the generalized curvilinear coordinate system. The dispersionrelation-preserving scheme is utilized for space discretization. The 2N storage low-dissipation and lowdispersion Runge-Kutta scheme is applied for time marching. Numerical results are presented at Mach number 1.38, 1.42 and 1.43 for two nozzle exit lip thicknesses of 0.625-in. and 0.4-in. It is shown that the predicted wavelengths of the apping and helical modes are in good agreement with experimental data by Ponton & Seiner. The predicted shock cell structure and radial density proles agree well with the measured results by Panda & Seasholtz. And the simulated non-axisymmetric screech apping phenomenon is also analyzed and qualatively compared with the acoustic measurement data by Ponton & Seiner.
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