某飞机系列风洞试验研究  

The series investigations on an aircraft in 4m×3m wind-tunnel

作　　者：祝明红[1] 陈洪[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《流体力学实验与测量》2003年第4期43-47,共5页Experiments and Measurements in Fluid Mechanics

摘　　要：介绍了某飞机在气动中心4m×3m风洞进行的系列风洞试验研究情况。研究目的是获得在不同布局状态下飞机的低速气动性能。研究结果表明:改变机翼边条可有效地改善飞机的纵向稳定性;将两侧进气改为腹部进气,大大降低了飞机的航向稳定性;采用机头边条措施可使飞机的航向稳定性有较大提高;进行通气模型的风洞试验,其结果与不通气时的结果差异不大。The series investigations on an aircraft were carried out in 4m×3m wind-tunnel.The aim is to obtain the low-speed aerodynamic characteristics on different configurations.The results show that the wing strakes can improve the longitudinal stability effectively;the yaw stability will be decreased considerably if the two-side-inlet is converted to abdomen-inlet;the nose strakes can improve the yaw stablility of aircraft largely;the results of TFN model have little differences from the non-TFN.

关 键 词：飞机 风洞实验 气动特性 航向稳定性 试验设备 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]