China Academy of Aerospace Aerodynamics,The Second Research Institute
远程宽体客机实际飞行状态下机翼变弯度有效减阻可以提升客机性能和飞行品质。以全机配平构型为研究对象，基于襟翼、扰流板偏转建立变弯度模型；采用RANS 方程实现阻力的精确求解并建立响应面模型，对不同升力系数、马赫数的多个飞行状态进行变弯度减阻优化；在此基础上，对实际飞行过程中变弯度操作需求及综合减阻性能进行分析，并采用布雷盖公式评估机翼变弯度后全航段综合巡航效率。结果表明：在巡航马赫数飞行时，采用两次变弯度设置即可在较宽的升力系数范围内获得减阻收益；在10 km 定高巡航时，机翼变弯度可使整个航段综合减阻1.9 cts（阻力系数单位），航时、航程提高0.72%；在8 和10 km 进行一次阶梯巡航，机翼变弯度可使整个航段综合减阻2.9 cts，航时、航程提高1.19%。
For the design of variable camber wing of long range wide-body civil aircraft, the trimmed configurations with flap and spoiler deflecting were researched, which can fully consider both the impact on trim characteristic and the feasibility of variable camber wing. The Reynolds averaged Navior-Stokes equations were solved to predict the drag precisely and the Response-surface models were built based on these results. The drag reduction optimizations were carried for multi-conditions with different lift coefficients and Mach numbers. The optimization results show that at cruise mach number, the camber variation can lead drag reduction except at lower lift condition, and at lower mach number the drag can also be reduced by camber variation. The optimal angles of flap for each flight condition are different. Based on the above-mentioned work, the requirement of camber variable manipulation and the general drag reduction were researched by numerical simulation. The results show that two camber settings can lead drag reduction in a large range of lift. The camber designed for cruise condition can still obtain drag reduction at lower mach number. The general profit of cruise efficiency was evaluated based on Breguet equation. When cruising at a fixed altitude of 10km, 1.9 cts of drag reduction and 0.72% increase of flight time and endurance can be obtained during the whole cruise phase. When cruising at stepped altitudes of 8km and 10km, 2.9 cts of drag reduction and 1.19% increase of flight time and endurance can be obtained.