Experimental studies and control of wall-bounded and separated shear layers using active flow control

航空航天部门在加拿大经济中发挥着重要作用。2017年，其GDP约占250亿美元，高薪就业岗位近19万个。就航空业而言，气候变化和噪音污染是其面临的一些最重大挑战，也是该行业面临的风险。为了使加拿大航空航天业保持全球竞争力，需要在技术上进行逐步改革。主动流量控制是被认为有助于满足国际航空运输协会（IATA）对航空航天工业设定的严格环境目标的技术之一。 拟议的研究将开发和实施新的主动流量控制策略，重点是与加拿大航空航天工业相关的流场。要研究的具体主动流动控制目标是：（i）减少紊流边界层引起的表面摩擦阻力，（ii）尾流控制，以减少钝后缘翼型的压阻和噪声排放。 (1)以前的研究表明，通过主动控制近壁湍流，湍流边界层中的表面摩擦减少了约30%。然而，最近的研究表明，这些好处不会按比例增加到飞行雷诺数。本文提出了一种新的控制湍流边界层的方法，即通过操纵对数区域中存在的大的相干结构来控制湍流边界层。已知这些结构在大雷诺数下变得更占主导地位，并且与近壁结构相比，由于其尺寸更大，因此可以提供更实用的实施途径。 (2)具有钝后缘的翼型在航空航天工业中是常见的，因为它们可以提供上级升阻比和改进的结构完整性。然而，与这些相关的尾流导致更高水平的压阻、波动的气动力和噪声。申请人对钝后缘流线型机身的初步研究证明了一种有效的主动流动控制方法，该方法使压阻减小约30%，尾流不稳定性减少90%以上。有人建议将这种方法推广到钝后缘翼型，使其更接近工业应用。这将导致这些翼型的性能显著改善。 这项研究的实际影响是重要的和广泛的。它们包括在各种商业相关流体系统中减少阻力、燃料消耗和噪音排放。这些好处将减少航空航天工业对化石燃料的依赖，并减少温室气体排放。这项研究也是变革性的，因为它解决了开放的问题，从长远来看，应该导致一个范式转变方面的设计实践的能源效率，减少污染，流体系统。

The aerospace sector plays an important role in the Canadian economy. In 2017, it accounted for approximately $25 billion in GDP and nearly 190,000 high-paying jobs. In the specific case of aviation, climate change and noise pollution represents some of its most significant challenges and are risks to the industry. In order for the Canadian aerospace industry to remain globally competitive, step changes in technology are required. Active flow control is one of the technologies considered to help meet the stringent environmental targets set on the aerospace industry by the International Air Transport Association (IATA). The proposed research will development and implementation novel active flow control strategies with an emphasis on flow fields that are relevant to the Canadian aerospace industry. Specific active flow control objectives to be investigated are: (i) reduction of skin-friction drag due to turbulent boundary layers, and (ii) wake control to decrease the pressure drag and noise emissions from blunt trailing edge airfoils. (1) Previous studies demonstrated ~30% reduction in skin friction in turbulent boundary layers through active control of the near-wall turbulence. However, recent works suggests that these benefits would not scale to flight Reynolds number. A new approach of controlling the turbulent boundary layer through the manipulation of the large coherent structures present in the log-region will be considered with this proposal. These structures are known to become more dominant at large Reynolds number and can offer a more practical pathway to implementation given their larger sizes compared to the near-wall structures. (2) Airfoils with blunt trailing edges are common in the aerospace industry since they can provide superior lift to drag ratios and improved structural integrity. However, the wake associated with these causes higher levels of pressure drag, fluctuating aerodynamic forces and noise. Preliminary studies by the applicant with a blunt trailing edge streamlined body demonstrated an effective active flow control methodology that produced a reduction in pressure drag of approximately 30% and over 90% less unsteadiness in the wake. It is proposed to take this methodology closer to industrial application by extending its use to blunt trailing edge airfoils. This will lead to significant better performance for these airfoils. The practical ramifications of this research are significant and wide ranging. They include the reduction of drag, fuel consumption and noise emissions in a variety of commercially relevant fluid systems. These benefits will lead to a reduction in the aerospace industry's dependence on fossil fuels and a decrease in greenhouse gas emissions. The research is also transformative since it addresses open questions that, in the long term, should lead to a paradigm shift with respect to the design practices for energy efficiency of, and pollution reduction from, fluidic systems.