发动机进排气效应对民机构型气动特性影响

发布时间：2019-05-27 02:43

【摘要】：基于非结构混合网格技术,通过数值求解Navier-Stokes方程,分析了航空发动机进排气效应对民机构型气动特性的影响。通过设置合适的进排气边界条件来模拟发动机进排气效应的影响,采用单独发动机短舱风洞试验模型,验证了计算方法的可靠性。在此基础上,分析了发动机进排气效应对翼吊式和尾吊式两种典型民机构型气动特性的影响,结果表明:翼吊式民机构型发动机进排气效应对升力的干扰主要由发动机尾喷流的引射效应对机翼的干扰引起;尾吊式民机构型随着发动机进气流量的增大,机翼上表面压力逐渐减小,激波位置逐渐后移;不同发动机进气流量会对飞机的阻力特性产生较大影响,在飞机详细设计阶段需充分考虑机体与动力装置之间的干扰影响。
[Abstract]:Based on the unstructured hybrid grid technique, the influence of the intake and exhaust effect of aero-engine on the aerodynamic characteristics of civil aircraft configuration is analyzed by solving the Navier-Stokes equation by numerical solution. The influence of engine intake and exhaust effect is simulated by setting appropriate intake and exhaust boundary conditions, and the reliability of the calculation method is verified by using a single engine short cabin wind tunnel test model. On this basis, the influence of engine intake and exhaust effect on the pneumatic characteristics of two typical civil aircraft configurations, wing hoisting type and tail suspension type, is analyzed. The results show that the interference of intake and exhaust effect on lift is mainly caused by the ejection effect of engine tail jet on the wing. With the increase of the intake flow rate of the engine, the pressure on the upper surface of the wing decreases and the shock wave position moves backward with the increase of the intake flow rate of the engine. The intake flow rate of different engines will have a great impact on the resistance characteristics of the aircraft, and the interference between the body and the power plant should be fully considered in the detailed design stage of the aircraft.
【作者单位】：中国空气动力研究与发展中心计算空气动力研究所;
【分类号】：V211;V231

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