A second-order method of characteristics (MOC) algorithm was used to determine the flow field and wall contour for supersonic axisymmetric, minimum length micro nozzles with a straight sonic line. Contours for axisymmetric supersonic micro nozzles were predicted with a stagnation pressure of 8 atmospheres. These profiles were then tested using a compressible Computational Fluid Dynamic (CFD) code. The CFD codes were also used to model pressure distribution and shock formation during the laser cutting and drilling mechanisms. Results obtained were compared with experimental analysis.
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