Computation of Sound Radiation in an AxisymmetricSupersonic Jet

  • Kim, Yong-Seok (Korea Automotive Technology Istitute) ;
  • Lee, Duck-Joo (Division of Aerospace Engineering, Department of Mechanical EngineeringKorea Advanced Institute of Science and Technology)
  • Published : 2004.12.31


An axisymmetric supersonic jet is simulated at a Mach number 2.1 and a Reynolds numberof 70000 to identify the mechanism of Mach wave generation and radiation from the jet. In orderto 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 ComputationalAeroAcoustics(CAA) techniques, is newly employed. Perfectly expanded supersonic jet is selectedas a target to see pure shear layer growth and Mach wave radiation without effect of change injet cross section due to expansion or shock wave generated at nozzle exit. The sound field ishighly directional and dominated by Mach waves generated near the end of potential core. Thenear field sound pressure levels as well as the aerodynamic properties of the jet, such asmean-flow parameters are in fare agreement with experimental data.



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