本文对翼尖小翼的飞行试验结果进行了分析,试图说明它对飞机的气动载荷、操稳特性及飞行性能的影响。此外还提出了在设计翼尖小翼时应着重考虑的问题。 飞行试验的结果表明,翼尖小翼可将巡航时的升阻此提高5～11％~[1],对侧向稳定性和副翼效率等性能无不利影响。将飞行试验结果与以升力面理论为基础的计算方法所得到的预测值进行了此较,大部分情况下有较好的一致性。 In this paper, the flight test results of wingtip winglets are analyzed in an attempt to illustrate its impact on aerodynamic loads, handling characteristics and flight performance of the aircraft. In addition, the problems that should be considered when designing the wingtips are also proposed. The results of the flight test show that the wingtip can increase the lift resistance during cruising by 5 to 11% [1] without adversely affecting the performance of lateral stability and aileron efficiency. This comparison is made between the flight test results and the predictions obtained from the calculation based on the theory of lift surfaces, and in most cases, it is in good agreement.