The dawn of research on shock and boundary layer interaction control dates back to the 1970s, when humped transonic aerofoils were first studied as a means to improve the performance of supercritical aerofoil technology at off-design conditions. Since then, shock control bumps have been found to be promising devices for such kind of flow control. They have a smearing effect on the shock wave structure achieved through isentropic pre-compression of the flow upstream of the main shock and can significantly lower wave drag without incurring unacceptable viscous losses. However, their performance is strongly dependent on a set of geometrical parameters which must be adjusted according to the ever-changing flight conditions. A concept for an adaptive shock control bump is therefore presented. The proposed actuation mechanism aims at a compact, lightweight and simple structure which could be integrated into the spoiler region of near-future aircraft without major design changes required. Numerical optimization of a simplified analytical model of the structure is used to investigate the shock control bump adaptation to various aerodynamic target shapes. Compromises between geometrical conformity and both structural and actuation related requirements are studied. Furthermore, an outlook is given on design issues related to three-dimensional effects on a finite span shock control bump.

中文翻译：

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使用加压室变形自适应冲击控制凸块

冲击和边界层相互作用控制研究的曙光可以追溯到 1970 年代，当时首次研究了驼峰跨音速翼型，作为在非设计条件下提高超临界翼型技术性能的一种手段。从那时起，人们发现冲击控制凸块是用于此类流量控制的有前途的设备。它们对通过主激波上游流动的等熵预压缩实现的激波结构具有拖尾效应，并且可以显着降低波阻而不会产生不可接受的粘性损失。然而，它们的性能在很大程度上取决于一组几何参数，这些参数必须根据不断变化的飞行条件进行调整。因此提出了自适应冲击控制冲击的概念。提议的驱动机制旨在紧凑、轻巧而简单的结构，可以集成到近期飞机的扰流板区域，无需进行重大的设计更改。结构的简化分析模型的数值优化用于研究冲击控制颠簸对各种气动目标形状的适应性。研究了几何一致性与结构和驱动相关要求之间的折衷。此外，还对与有限跨距冲击控制凸块的三维效应相关的设计问题进行了展望。研究了几何一致性与结构和驱动相关要求之间的折衷。此外，还对与有限跨距冲击控制凸块的三维效应相关的设计问题进行了展望。研究了几何一致性与结构和驱动相关要求之间的折衷。此外，还对与有限跨距冲击控制凸块的三维效应相关的设计问题进行了展望。