后掠翼模型混合层流控制实验研究

利用前缘吸气和顺压梯度，在对称后掠机翼模型上，实现了混合层流控制。在连续式跨声速风洞中，研究了气流马赫数和雷诺数对转捩位置的影响，研究了前缘吸气流量及流量分配对层流控制效果的影响。实验过程中，利用壁面冷却方法，扩大了层流区和湍流区的壁面温度差，利用埋入式安装的热电偶测量了表面温度分布，确定了转捩位置和层流区范围。结果表明，前缘吸气具有良好的层流控制效果，可以使层流区范围显著扩大。前腔吸气流量对层流控制效果影响很大，后腔吸气流量影响较小。

Hybrid laminar flow control experiment on swept wing model

Hybrid laminar flow control （HLFC） was implemented on the symmetry swept wings model using the leading edge suction and favorable pressure gradient. The experiment was operated in a continuous transonic wind tunnel. The effects of Mach number and Reynolds number on transition location were studied. Meanwhile, the effect of leading edge suction flow rates and its distribution on the laminar flow control was analyzed. The wall temperature difference between laminar region and turbulent region was expanded using a wall cooling method in the experiment. The temperature distribution is obtained by the thermocouples embedded in the surface of model, consequently the transition location and the laminar flow region were determined. The resuits show that there is a good control effectiveness on laminar flow control by the leading edge suction; hence laminar flow area can be significantly expanded. The impacts of the front chamber suction on the laminar flow control are much greater than those of the other.