某飞机系列风洞试验研究

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

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.