Yong Seok Kim, Duck Joo Lee
International Journal of Aeronautical and Space Sicences, vol. 5, no. 2, pp.18-27, 2004

Abstract : An axisymmetric supersonic jet is simulated at a Mach number 2.1 and a Reynolds number of 70000 to identify the mechanism of Mach wave generation and radiation from the jet. In order to provide the near-field radiated sound directly and resolve the large-scale vortices highly, high-resolution essentially non-oscillatory(ENO) scheme, which is one of the Computational AeroAcoustics(CAA) techniques. is newly employed. Perfectly expanded supersonic jet is selected as a target to see pure shear layer growth and Mach wave radiation without effect of change in jet cross section due to expansion or shock wave generated at nozzle exit. The sound field is highly directional and dominated by Mach waves generated near the end of potential core. The near field sound pressure levels as well as the aerodynamic properties of the jet. such as mean-flow parameters are in fare agreement with experimental data

Keyword : No keyword