FL-61结冰风洞热气防冰系统试验方法研究

Experimental Research on a Hot Air Anti-icing System in FL-61 Icing Wind Tunnel

以典型运输类飞机翼面热气防冰系统为研究对象,发展了热气防冰系统冰风洞试验方法。冰风洞试验在航空工业气动院FL-61结冰风洞进行,完成了热气防冰系统重复性试验、干空气防冰性能试验、湿空气防冰性能试验。试验过程中热气防冰系统处于完全蒸发状态,得到了热气防冰系统表面温度分布,干空气条件下表面温度最大重复性误差2.1℃,湿空气条件下表面温度最大重复性误差3.8℃,冰风洞试验重复性良好。与干空气条件相比,湿空气条件下前缘蒙皮表面温度均出现明显下降,最高温度相差达到18.3℃。

Icing wind tunnel test method on a hot air anti-icing system was developed based on a transport aircraft wing section.A hybrid wing model equipped with a hot-air ice protection system was tested at the FL-61 icing wind tunnel in AVIC ARI for a range of conditions representative of in-flight icing.Icing wind tunnel repeatability,dry air performance and wet air performance were researched.Test results show that the hot air anti-icing system performed as a fully evaporated system without running back water,and surface temperature was documented,the maximum temperature repeatability variation was 2.1℃at dry condition and 3.8℃at wet condition,which represent a good icing wind tunnel repeatability.Wet test cases resulted in significantly lower skin temperatures compared to dry test cases,and the maximum temperature variation was 18.3℃.