Plasma actuation for improved aircraft aerodynamics

这项研究计划是机械工程系的研究人员之间的合作 蒙特雷亚尔理工学院和印度航空航天工程学院 技术-坎普尔(IIT-K)。它由三个项目组成，涉及使用等离子致动器进行流量控制。流动 控制包括在战略位置放置相对低功率的执行器，使其具有不成比例的大小 对流场的影响。等离子体致动器是一种最新的电流体技术，能够将 电能直接转化为流动的动量，而不需要任何运动部件。它是通过部分空气电离来实现的 在两个平行但偏置的电极之间施加高电压(但功率很低)。 一种介电材料。这种固态、轻、薄、简单、纯电动的驱动器具有高带宽和 易于集成，从而提供了第一个实际广泛使用的流控制，从而潜在地带来了革命性的 飞机空气动力学。 研究的第一个项目旨在延迟飞机表面的层流-湍流边界层转变。 带有等离子致动器，以减少粘性阻力。第二个项目将调查对 翼型大迎角附面层分离提高翼型襟翼性能的研究 短期内，并最终完全移除机翼、板条和扰流板。第三个项目是开发 改变附面良好的小迎角机翼和尾翼升力的两个新概念 用等离子体激励器依次修正翼尖涡和训练边缘流曲率的层数 取消所有可移动的飞行操纵面。 蒙特雷亚尔理工学院将负责建立和实施所有风洞验证 所有三个项目的实验以及项目3中的一些数值模拟，而IIT-K将 负责项目1、2及部分项目3的全部计算工作。

This research program is a collaboration between researchers in the Department of Mechanical Engineering at École Polytechnique de Montréal and in the Department of Aerospace Engineering at the Indian Institute of Technology-Kanpur (IIT-K). It consists of three projects involving flow control using plasma actuators. Flow control consists of placing relatively low-power actuators at strategic locations to have disproportionally large effects on the flow field. A plasma actuator is a recent electro-fluidic technology capable of converting electricity directly into flow momentum without any moving parts. It does so via partial air ionization through the application of high voltages (but at very low power) between two parallel but offset electrodes separated by a dielectric material. This solid-state, light, thin, simple and purely electrical actuator has high bandwidth and is easy to integrate thus offering the first practical widespread use of flow control to potentially revolutionize aircraft aerodynamics. The first project of the research aims to delay laminar-turbulent boundary layer transition on aircraft surfaces with plasma actuators in order to reduce viscous drag. The second project will investigate the control of boundary layer separation on airfoils at high angles of attack to increase the effectiveness of airfoil flaps in the short term and eventually to remove wing flaps, slats and spoilers altogether. The third project is to develop two new concepts to change lift on wings and empenages at low angles of attack with well-attached boundary layers via modification of the wing tip vortex and trainling edge flow curvature with plasma actuators in order to eliminate all movable flight control surfaces. École Polytechnique de Montréal will be responsible for setting up and carrying out all wind tunnel validation experiments in all three projects as well as some numerical simulations in project 3 while IIT-K will be responsible for all computational work in projects 1 and 2 and part of project 3.