Numerical Study on Aerodynamic Performance of CK Drone Aircraft Air Inlet in Maneuvering Flight  

机动飞行时长空靶机进气道气动性能数值研究

作　　者：CAO Guangzhou LI Bo LIANG Shibo TAN Hongming 曹广州;李博;梁世波;谭红明(南京航空航天大学中小型无人机先进技术工业和信息化部重点实验室,南京210016;南京航空航天大学能源与动力学院,南京210016)

机构地区：[1]Key Laboratory of Advanced Technology for Small and MediumSized UAV,Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,P.R.China [2]College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,P.R.China

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2020年第5期739-749,共11页南京航空航天大学学报（英文版）

基　　金：supported by the Fundamental Research Funds for the Central Universities(No.56XCA2004806)。

摘　　要：In view of the engineering background that CK drone aircraft needs modification and upgrading to improve its maneuvering performance,numerical research and analysis of air inlet aerodynamic performance are carried out.Firstly,based on the introduction of the theoretical knowledge involved in aircraft maneuvering flight,parameters such as aircraft attitude and engine mass flow etc.required for the aerodynamic performance calculation of CK drone aircraft air inlet are determined.By analyzing the test data of WP6 engine inlet distortion simulation board,the typical indexes are extracted as the basis for evaluating the air inlet performance of CK drone aircraft.Then,the aerodynamic characteristics of the inlet of CK drone aircraft under different maneuvering conditions are numerically studied,and the total pressure recovery coefficient and pressure distortion index of the outlet section are obtained.Several conclusions and suggestions are formed after the study.When CK drone aircraft flies at positive angle of attack,the inlet has good aerodynamic characteristics,which can meet the requirements of engine intake during high maneuverable flight.In the flight of negative angle of attack,the total pressure loss and pressure distortion at the outlet section of air inlet increase sharply,which cannot guarantee the stable working of the engine.On the premise that the aircraft attitude is satisfied,CK drone aircraft can use three engine thrust states of"Rated","Modified rated"and"Maximum"for high maneuverable flight.针对CK靶机需要改型升级以提高其机动性能的工程背景,开展进气道气动性能的数值研究和分析。首先在介绍机动飞行所涉及理论知识的基础上,确定了CK靶机进气道气动性能计算所需的飞机姿态和发动机流量等参数;通过分析WP6发动机进气道畸变模拟板试验数据,提炼典型指标作为CK靶机进气道性能评判的依据。之后数值研究了CK靶机的进气道在不同机动状态下的气动特性,得到了出口截面的总压恢复系数和压力畸变指数等。经过研究形成几点结论和建议:CK靶机在正迎角飞行时,进气道具有良好的气动特性,可以满足高机动飞行时发动机的进气需求;在负迎角飞行时,进气道出口的总压损失和压力畸变都急剧增加,不能保证发动机的稳定工作;在飞机姿态满足的前提下,CK靶机可以使用"额定""修正额定"和"最大"3种发动机状态进行机动飞行。

关 键 词：CK drone aircraft high maneuvering flight suspended nacelle inlet total pressure recovery coefficient pressure distortion index 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]