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An Euler flow analysis of turbine powered simulator (TPS) and fanjet engine was made utilizing MacCormack's finite volume scheme. TPS simulation computations for an axisymmetric geometry were compared with experimental data obtained in the National Aerospace Laboratory transonic wind tunnel. The pressure distributions on the inlet cowl and corejet cowl surfaces showed excellent agreement. The effect of differences in engine conditions of corejet temperature and mass flux between the TPS flow and a real fanjet engine was analyzed with the computations. The results showed no significant differences in the external flowfield surrounding the exhaust jet plume. A three-dimensional analysis showed the effects of angle of attack on the inlet flowfield and exhaust jet plume.
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Hirose et al. (1991) studied this question.
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