In this thesis, the screech tone of underexpanded jet is numerically calculated without any specific modeling for the screech tone itself. Fourth-order optimized compact scheme and fourth-order Runge-Kutta method are used to solve the 2D axisymmetric Euler equation. Adaptive nonlinear artificial dissipation model and generalized characteristic boundary condition are also used. To validate the developed code, two kinds of problem are solved. One is the pulse jet problem, and the other is perfectly expanded jet problem of Mach number 2.1. The numerical analyses of both problems have almost same results with experiments and other simulations around near field for each case. The screech tone, generated by a closed loop between instability waves and quasi-periodic shock cells at the near field, is reasonably analyzed with present numerical methods for the underexpanded jet having Mach number 1.2 at the exit. The instantaneous density contour plot shows Mach waves due to mixing layer convecting supersonically, which propagate downstream. For the underexpanded jet case, the screech tone propagating upstream is observed very clearly. The calculated screech tone frequency has good agreements with experiment and theoretical result. It can be concluded that the basic phenomenon of screech tone including the frequency can be calculated by using high-order and high-resolution schemes without any specific numerical modeling for screech tone feedback loop.
