翼吊短舱形式运输机进气道阻力特性分析方法研究  

Study on Intake Drag Characteristics of Transport Airplane with Powered-on Aeroengine in Nacelle

作　　者：高翔[1] 李密[1] 李秋锋[1] GAO Xiang;LI Mi;LI Qiu-feng(Aeroengine Research Institute,Chinese Flight Test Establishment,Xi'an 710089,China)

机构地区：[1]中国飞行试验研究院发动机所,陕西西安710089

出　　处：《推进技术》2019年第1期61-68,共8页Journal of Propulsion Technology

摘　　要：为了解决飞机/发动机一体化设计中进气道阻力确定的问题,以典型带动力装置运输机为研究对象,建立了其三维实体模型,开展了不同飞行高度、不同飞行马赫数及不同发动机状态的数值计算。根据计算结果,建立了进气系统阻力增量的确定方法,总结了附加前体力与短舱前罩力随捕获面积比、飞行高度、飞行马赫数的变化规律。结果表明:在AGARD-CP-150中的推力/阻力体系划分方法基础上,发动机状态及捕获面积比的改变会引起进气道阻力变化,飞行高度对短舱前罩力及附加前体力系数没有影响。Three-dimesional model has been carried out based on a typical transport airplane for the purpose of exploring intake drag determination method in integrated design of airplane and aeroengine.Numerical calculations were conducted for different flight altitudes,Mach numbers and engine conditions based on the flight test data.According to the numerical results,determination method of intake drag increment was put forward and variation of addtional front force and nacelle front force with capture area ratio,flight altitude and Mach number was summarized.Simulation results show that the change of engine power condition and capature area ratio leads to the variation of intake drag.However,flight altitude has no effects on nacelle front force coefficients and additional front force coefficients according to the thrust/drag division method in AGARD-CP-150.

关 键 词：运输机 数值计算 附加前体力 短舱前罩力 升阻极曲线 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]