翼吊短舱形式发动机推/阻划分的风洞试验研究

Thrust/Drag Division for Powered-on Aeroengine in Nacelle by Wind-Tunnel Test

关键词:  气动特性  缩比模型  风洞试验  推/阻力划分  短舱

Key words:  Aerodynamic characteristics  Scale model  Wing-tunnel test  Division of thrust and drag  Nacelle

摘要:

为了确定在实际飞行条件下，当发动机状态变化时，进排气系统损失对飞机气动特性的影响，针对翼吊短舱形式的发动机开展了缩比模型风洞试验，分别进行了巡航构型与起飞构型，马赫数0.1，0.15，0.2，攻角0°~15°，发动机外涵喷管落压比1.22，1.32，1.44，1.53，1.61等条件下的风洞试验。通过数据分析，明确了该类型发动机推/阻划分的基本方法，分析了发动机状态变化时飞机气动特性的改变及修正方法。风洞试验结果表明：发动机状态变化对飞机升阻特性影响明显，必须建立合理的推/阻划分体系，对实际使用条件下，发动机状态变化引起的进排气损失进行修正，通过本文建立的推/阻划分体系，计算得到的发动机安装净推力与风洞试验结果最大偏差为1.6%。

Abstract:

In order to determine the inlet and exhaust loss effect on airplane aerodynamic characteristics under different aeroengine power settings in actual flight condition， scale model wind-tunnel test was conducted for the powered-on aeroengine in nacelle. The wind-tunnel test was conducted under cruise and take-off configurations with mach numer 0.1， 0.15， 0.2， angle of attack 0°~15°， and bypass pressure ratio 1.22， 1.32， 1.44， 1.53， 1.61. Through test data analysis， division method of thrust and drag was put forward， and the correction method for the change of airplane lift/drag characteristic under different engine power settings was established. Wind-tunnel results show that： the change of engine power setting has significant effects on airplane aerodynamic characteristics. Reasonable division method of thrust and drag must be conducted， then the corrections of inlet and exhaust loss for different engine power settings under real working condition should be conducted. Under the division method of thrust and drag in this article， the maximum deviation between calculated aeroengine installed net thrust and wind-tunnel result is 1.6%.