Abstract
A numerical method (inverse method) was developed for a gas-particle supersonic flow past two-dimensional blunt bodies. This method is based on two transformations (von Mises and additional one), which are convenient for determining the shock layer flow fields and the body shapes. Using the present method, the pure gas flow field around a circular cylinder was first solved numerically for the freestream Mach numbers M∞=2.0 and 3.0. Then the gas-particle flow in the shock layer around blunt bodies (nearly circular cylinders) was solved for freestream Mach number M∞=3.0, with particle diameter dp 2, 5, 10 μm and freestream loading ratios α=0, 0.2, 0.5 and 1.0, respectively. The effects of dp and α on the shock stand-off distance, the body surface pressure and flow quantities along the stagnation streamline are discussed, and the flow patterns in the shock layers are also shown.
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