针对单发鸭式布局飞机，通过低速风洞试验，研究了矢量喷流对飞机大迎角气动力的影响特性。研究结果表明：发动机喷口直径变大使得飞机大迎角升力和阻力系数增加，并产生低头力矩系数。喷流使得飞机大迎角升力和阻力系数明显增加，并产生低头力矩系数；大喷口状态喷流影响比小喷口状态高50%左右。发动机喷管上/下偏转时，矢量喷流对飞机上下表面气流诱导不对称，喷管上偏减小升力和阻力系数、产生抬头力矩系数，喷管下偏增加升力和阻力系数、产生低头力矩系数，且喷管下偏影响明显比上偏大。在此基础上，基于数值模拟结果对喷流与飞机主流的相互作用机理进行了分析。
An experimental study on single-engine canard aircraft interactive behaviors between the vectoring jet and aerodynamics at high angles of attack is conducted in a low-speed wind tunnel. The test results indicate that increase in the engine nozzle diameter can enhance the lift and drag coefficient and produce pitch down moment at high angles of attack. Jets can significantly increase the lift and drag coefficient and also produce pitch down moment at high angles of attack. However, the increment of lift or drag and decrease of pitching caused by the jet is 50% less in case of a small nozzle than in case of a large nozzle. When the vectoring engine nozzle is deflected upward or downward, the airflows induced by the vectoring jets on the upper and lower surfaces of the aircraft are asymmetrical. The lift and drag coefficient decrease and the pitching moment increases when the jet is deflected upward, and the opposite is true when the jet is deflected downward. In addition, the effect of jets deflecting downward is noticeably larger than that of jets deflecting upward. Based on this, the flow field mechanism of interactive behaviors between the vectoring jet and the main flows is analyzed by numerical simulation.
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