Abstract
We present simulation results for oscillatory modes in supersonic flow past an aircraft with a hypersonic jet engine. The flow of viscous compressible gas is modeled by a quasi-gas dynamic (QGD) system of equations. A coordinate transformation is applied to adapt the computational region to the configuration of the compression shock in supersonic flow past an object. An original method is proposed for the introduction of additional dissipation that smooths the instability in the neighborhood of the compression shock. The spectral characteristics of the oscillatory flow in the turbulence region follow the Kolmogorov law of oscillation energy decrease with increasing oscillation frequency.
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