共轴刚性旋翼直升机桨毂阻力特性试验

共轴刚性旋翼直升机在突破常规直升机前飞速度极限的同时会产生巨大的桨毂阻力。为研究共轴刚性旋翼直升机桨毂的阻力特性,采用天平测力的方式在1.4m×1.4m直流风洞中对不同的共轴双桨毂组合模型进行了风洞试验。试验状态变量包括桨毂转速、模型各部件间缝隙和不同整流模型组合。试验结果表明:共轴双桨毂试验模型的阻力受对称光滑桨毂旋转运动的影响基本可忽略;各整流部件间缝隙对模型所受阻力影响较大,大缝隙会使试验模型阻力增大;各整流部件分离尾流存在较大的气动干扰,使模型所受阻力明显增加。

Drag Characteristic Test for Hub of Coaxial-Rigid-Rotor Helicopter

Coaxial-rigid-rotor helicopter has a huge hub drag in forward flight. In order to analyze the drag characteristics of the hub, a test research using force balance is completed in a 1.4 m×1.4 m wind tunnel. Test variations include wind speed, hub rotating speed, hub model gap and different fairing groups. Test results show that the drag of coaxial hub test model affected by the symmetric smooth hub rotation can be ignored; the gaps between the fairing components have a great influence on the drag of models, and the big gap causes the drag increasing; the separated flow after every fairing component produces strong aerodynamic interaction between each other, and makes the drag increase obviously.