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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.
In view of the influence of the civil aircraft lifting device on the aerodynamic characteristics of the wing, a wind tunnel test on chirp-shaped swept half-mold lifting device of a certain passenger aircraft at the NH-2 low-speed wind tunnel of Nanjing University of Aeronautics and Astronautics is carried out. The flow Mach number is 0.2 and the experimental Reynolds number based on the aerodynamic chord length of the wing is 1.85 × 106. Through the test results, it is emphatically analyzed that the trailing edge flap angle, The optimal combination parameters of the deflection angles and the slits of the slats are obtained.The results show that the deflection angle of the slats and the width of the slits are the main parameters that affect the aerodynamic characteristics of the wing, The smaller the impact is; the suitable slit width can bring larger lift coefficient and lift resistance. When the width of the slat track is 2%, the lift characteristic is the best. When the width of the slat track is 1%, the lift resistance is relatively large .