自然层流翼套方案设计及飞行测试验证

Design and flight test verification of natural laminar flow wing glove

为了提高层流机翼设计和测试的技术成熟度,开展了全尺寸验证机层流翼套的气动设计和飞行试验。将可以预测常见的T-S波和C-F波诱导转捩的e^(N)方法与RANS方法耦合,建立考虑转捩位置的数值模拟方法,基于翼套设计方案开展翼套设计和单侧翼套飞行验证机起降状态失速特性及横航向稳定性分析,以及不同飞行状态下转捩位置及影响规律研究。单侧机翼加装翼套后,自然层流验证机失速迎角减小约1.5°,俯仰力矩系数增加约0.01,力矩斜率基本不变。数值仿真结果与飞行试验结果对比分析表明两者压力分布重合良好,设计状态下层流区长度均大于45%当地弦长。通过飞行测试红外图像及压力分布研究转捩影响规律显示:相同马赫数下,随着迎角的增加,顺压梯度和层流区逐渐减小;相同高度下,随着马赫数的增加,顺压梯度和层流区逐渐增加。

In order to increase the TRL of laminar wing design and flight measurement,the aerodynamic design and flight tests of the wing glove for the full-size demonstrator aircraft were performed.The eN method which can predict the transition induced by T-S wave and C-F wave was coupled with the RANS method,and a numerical simulation tool was established.Based on this method and de-sign scheme,the wing glove was designed,and the stall characteristics and transverse heading sta-bility of the one-sided wing glove flight verification aircraft in takeoff and landing configuration,as well as the transition position and influence law under different flight configurations were studied.After installing wing glove on one side of the wing,the stall angle of attack of the natural laminar flow verifier decreases by 1.5°around,the pitching moment coefficient increases by 0.01 around,and the moment slope is basically unchanged.Comparing the numerical simulation results with the flight test results,the coincidence degree of the pressure distribution patterns is well,and the length of the laminar flow zone in the design state is greater than 45%chord.The transition effect law is studied by flight test infrared image and pressure distribution.The results show that with the same Mach number,the favorable pressure gradient and laminar flow region gradually decreases with the increase of angle of attack;at the same altitude,the favorable pressure gradient and laminar flow region increases with the increase of Mach number.