摘要
以某型螺旋桨运输机带动力装置飞行试验台为研究对象,建立了三维流场模型,采用CFD进行了网格划分及数值计算。以前期飞行试验数据和发动机热力循环模型计算结果为边界条件,开展了不同飞行马赫数、高度及桨叶角的数值计算。选用桨叶角表征发动机状态,分析了不同飞行高度、马赫数、螺旋滑流对进气道前罩作用力和附加前体力影响的变化规律。计算结果表明:不同高度、桨叶角及马赫数均会改变进气道阻力,在马赫数0.5,高度4 km状态下,桨叶角由40°增大至50°,前罩作用力减小1700 N,附加前体力减小3600 N,而附加前体力系数及前罩作用力系数随飞行高度基本不变。进气道阻力特性研究为后续试飞中确定涡桨发动机外部阻力特性分析提供了数据支持。
Taking a certain type of propeller transport aircraft powered device flight test bed as the research object,a three-dimensional flow field model is established by CFD method with numerical calculation and meshing.The previous flight test data and engine thermal cycle model output data are used as boundary condition computational.Numerical calculations of different Mach,flight altitudes and blade angle are carried out.The engine state being characterized by the blade angle,the influence of different altitudes,speeds and blade angles on the force of the inlet front cover and additional front body force are analyzed.The calculation results show that at different altitude,the resistance of the inlet might be changed with the blade angle and Mach.When state is at 0.5 Mach and height equalsto 6 km,the blade angle increases from 40 to 50,the nacelle front force decreases by 1700 N,and the additional front drag decreases by 3600 N.While the flight altitude has almost no effect on the additional front body force coefficient and the front cover force coefficient.The research provides data support for determining the external resistance characteristics of the turboprop engine in the subsequent flight test.
作者
王定奇
WANG Dingqi(Power-Plant Flight Test Technology Institute,Chinese Flight Test Establishment,Xi’an 710089,China)
出处
《空军工程大学学报》
CSCD
北大核心
2023年第1期68-75,共8页
Journal of Air Force Engineering University
关键词
飞行试验台
数值计算
螺旋桨滑流
前罩作用力
附加前体力
捕获面积比
flight test bed
numerical simulation
slipstream of propeller
nacelle front force
additional front drag
capture area ratio
