S弯进气道能提高飞行器的隐身性能,但也带来了更大的进气损失,兼顾气动和隐身性能的进气道设计成为了研究难点。为此使用曲率控制的方法设计生成了椭圆、梯形、D形以及矩形共四种进口形式的双S弯进气道,利用CFD和快速多极子方法开展了...S弯进气道能提高飞行器的隐身性能,但也带来了更大的进气损失,兼顾气动和隐身性能的进气道设计成为了研究难点。为此使用曲率控制的方法设计生成了椭圆、梯形、D形以及矩形共四种进口形式的双S弯进气道,利用CFD和快速多极子方法开展了进口形式对双S弯进气道的气动性能和雷达散射特性的数值仿真研究。研究结果表明:椭圆形进口具有较低的周向畸变指数,梯形进口在小攻角下周向畸变指数低于D形进口,大攻角下两者性能相似;梯形进口在水平探测面上具有较低的RCS,比其余进气道模型至少低1.38 d Bsm,相比椭圆进口在周向综合畸变增加不到0.29%的情况下,RCS最大可降低2.54 d Bsm。展开更多
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...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.展开更多
文摘S弯进气道能提高飞行器的隐身性能,但也带来了更大的进气损失,兼顾气动和隐身性能的进气道设计成为了研究难点。为此使用曲率控制的方法设计生成了椭圆、梯形、D形以及矩形共四种进口形式的双S弯进气道,利用CFD和快速多极子方法开展了进口形式对双S弯进气道的气动性能和雷达散射特性的数值仿真研究。研究结果表明:椭圆形进口具有较低的周向畸变指数,梯形进口在小攻角下周向畸变指数低于D形进口,大攻角下两者性能相似;梯形进口在水平探测面上具有较低的RCS,比其余进气道模型至少低1.38 d Bsm,相比椭圆进口在周向综合畸变增加不到0.29%的情况下,RCS最大可降低2.54 d Bsm。
基金supported by the Fundamental Research Funds for the Central Universities(No.56XCA2004806)。
文摘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.
