螺旋桨滑流与平尾深失速效应耦合影响试验研究

本文采用螺旋桨飞机动力模拟风洞试验技术，研究常规布局涡桨飞机的螺旋桨滑流在大迎角条件下对飞机纵向气动特性的影响规律。中航气动院FL-9风洞中通过伺服电机驱动螺旋桨转动进行螺旋桨动力模拟风洞试验，试验迎角范围0°~50°，试验风速范围为30~50m/s。为了获得大迎角试验数据，常规迎角试验采用常规单支杆进行试验，大迎角试验采用带预弯的支杆进行试验。利用螺旋桨滑流风洞试验研究在大迎角时平尾深失速效应与滑流的耦合影响规律。研究结果表明，螺旋桨滑流会使得试验模型升力和阻力增加，纵向静稳定性降低，并且在大迎角条件下依然满足这些规律。此外，在较大迎角时平尾进入滑流与机翼洗流的耦合影响区域后，滑流会使得平尾失速效应加剧并且平尾更难从失速状态中改出，即受平尾深失速影响的迎角范围会更大且平尾深失速效应加剧。

Experimental research on the coupling effect of propeller slipstream and flat tail deep stall on aerodynamic characteristics of airplane

The influence of propeller slipstream on aerodynamic characteristics of conventional layout turboprop aircraft is studied at large attack angle by using propeller aircraft dynamic simulation test. The dynamic simulation test is curried out in FL-9 wind tunnel of Aerodynamics Research Institute of AVIC. The propeller is driven by servo motor. The test angle of attack range is 0°~50°, and the wind speed range is 30~50m/s. The conventional single strut is used at the normal attack angle test, while the special prebending strut is used at the large attack angle test. The coupling effect of flat tail deep install and propeller slipstream is studied detailedly. The test results show that the propeller slipstream increases lift and drag forces of the test model, and decreases the longitudinal static stability, and these features also exist at large attack angel test. In addition, the slipstream will make the deep stall effect of flat tail worse, and the flat tail will be harder to get out of stall when the flat tail entering the coupling influence area of slipstream and wing wash flow at the large angle test condition. That means the range of attack angle effected by deep stall will be larger and flat tail deep stall effect is aggravated.