Transonic 3-D Euler flow analysis code for fan-jet engine and Turbine Powered Simulator (T. P. S.) wind tunnel testing was developed utilizing MacCormack's scheme in finite volume form. The purpose is to validate the T. P. S. testing method at NAL Transonic Wind Tunnel developed for the Experimental STOL Plane 'Aska' and other transport aircraft testings as well as to analyze the fan-jet engine flow field. Comparison of the computations with an experimental data for a preliminary axisymmetric T, P. S. configuration was made. The pressure distributions on the inlet cowl and core-jet cowl surfaces show an excellent agreement. The effects of the engine condition difference between the real fan-jet engine and T. P. S. simulation: jet temperature and massflux relations, were analyzed. The result shows little differences in the external flow field surrounding the exhaust-jet plume. 3-D flow analysis was also made and it revealed angle of attack effects in the inlet flow field and exhaust-jet plume. A pair of longitudinal vortex was observed in the shear layer between the jet and the external flows.
|出版ステータス||Published - 1989 1 1|
|イベント||AIAA 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1989 - Buffalo, United States|
継続期間: 1989 6 12 → 1989 6 14
|Other||AIAA 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1989|
|Period||89/6/12 → 89/6/14|
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