民用飞机后缘增升装置气动力特性SCCH试验研究

The Research of Flap Aerodynamic Characteristic of an Airplane High-Lift Configuration in Wind-Tunnel with SCCH Model

针对民用飞机增升装置对机翼气动力特性的影响,在南京航空航天大学的NH-2低速风洞开展了某型号客机等弦长后掠半模增升装置测力风洞试验研究.试验来流马赫数为0.2,基于机翼气动弦长的试验雷诺数为1.85×106.通过试验结果,重点分析了后缘襟翼偏角、缝道宽度及缝道搭接量对机翼增升装置增升效率的影响,得到了襟翼偏角和缝道的最佳组合参数.研究结果表明:襟翼偏角和缝道宽度是影响机翼气动力特性的主要参数,缝道搭接量的影响较小;合适的缝道宽度能带来较大的升力系数和升阻特性,襟翼缝道宽度为2%时升力特性最佳,襟翼缝道宽度为1%时升阻比较大.

Focusing the influence of an airplane high-lift configuration on wing aerodynamic characteristics, an experiment was conducted in NH-2 low-speed wind tunnel over a civil aircraft SCCH high-lift configuration. In this experiment,Mach number is 0. 2 and Reynolds number is 1. 85 × 106. The effect of flap deployment angle,gap width and over-lap on efficiency of high-lift configuration is investigated. Based on the test results,best flap parameters of this model are obtained. The results show that the flap deployment angle and the gap width are the important factor for flap,while the over-lap has little influence. Appropriate gap width can help the flap get good lift coefficient and lift-to-drag ratio. For this model,the best lift characteristic can be get when the flap gap width is 2%. The lift-to-drag ratio has good performance when the flap gap width is 1%.