Non-uniform ENO Scheme for Simulation of Supersonic F

Abstract

The third order finite-difference shock-capturing essentially non-oscillatory (ENO)
scheme for a non-uniform grid has been developed. The design of the ENO scheme is based on
the methodology for uniform grids. The efficiency of the developed algorithm is demonstrated by
the numerical experiments on the simulation of the three-dimensional turbulent steady flowfield
generated by the transverse hydrogen injection into the supersonic air cross-flow. The analysis of
the different variations of the limiter functions for the developed algorithm is provided to define the
optimal function producing the smallest spread of the solution. The effect of the limiter choice on the
mixing layer dynamics is studied for the non-uniform grid. The numerical experiments revealed that
the nonoptimal choice of limiter can result in the overgrowth of the mixing layer, that is important
for the numerical modeling of the combustion.