摘要
针对尾部螺旋桨推进式无人机的流道布局特点,兼顾飞行器总体气动、总体结构、雷达隐身等方面的限制因素,设计了1种具有双90°偏折特征的进气道/蜗壳流道构型,并对其在地面抽吸工况下的气动性能和内部流动特征开展了仿真与试验研究。研究表明:蜗壳出口马赫数在0.4~0.6范围内,总压恢复系数均保持在0.97以上,总压畸变小于1.30%,为此流道构型气动性能良好。然而,在进气道/蜗壳耦合流动作用下,出口截面形成了显著的旋流流动,研究范围内平均旋流强度为9.90°~11.35°,旋流角大于15°的面积占比达到了20.4%~30.6%。分析发现,进气道因流道剧烈弯曲而引起的蜗壳非均匀进气条件,是驱动蜗壳内形成强横向二次流与分离涡,进而导致出口强旋流流动的主要原因。
An inlet/volute flow channel configuration with double 90°deflection characteristics is designed based on the inlet layout characteristics of the tail-propelled UAV,taking into account the constraints of the overall aerodynamics,overall structure,radar stealth and other aspects of the aircraft.Its aerodynamic performance and internal flow charac⁃teristics are simulated and tested under ground-based suction conditions.The results show that the Mach number at the outlet of the volute is in the range of 0.4 to 0.6,the total pressure recovery coefficient is kept above 0.97,and the value of total pressure distortion is smaller than 1.30%,demonstrating good aerodynamic performance of the inlet con⁃figuration.However,the outlet section forms a significant vortex flow under the effect of inlet/volute coupling flow.The average swirl intensity in the study range is 9.90°-11.35°,and the proportion of area with an absolute swirl angle greater than 15°reaches 20.4%-30.6%.It is found that the non-uniform inlet condition of the volute caused by the severe deflection of the inlet passage is the main reason for the formation of strong transverse secondary flow and separation vortex in the volute,thus leading to the strong swirling flow at the outlet.
作者
郑高杰
何小明
李东坡
谭慧俊
汪昆
吴祯龙
王德鹏
ZHENG Gaojie;HE Xiaoming;LI Dongpo;TAN Huijun;WANG Kun;WU Zhenlong;WANG Depeng(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AVIC(CHENGDU)Unmanned Aerial Vehicle System Co.,Ltd.,Chengdu 610000,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2024年第4期172-185,共14页
Acta Aeronautica et Astronautica Sinica
基金
国家杰出青年科学基金(12025202)
民用飞机专项科研项目(MJ-2020-F-10)。
关键词
双90°偏折
进气道
蜗壳
旋流
无人机(UAV)
double 90-degree deflection
inlet
volute
swirling flow
Unmanned Aerial Vehicle(UAV)
