Plasma actuation for improved aircraft aerodynamics

等离子驱动可改善飞机空气动力学

• 批准号: 460936-2013
• 负责人: Vo, HuuDuc
• 金额: $ 1.89万
• 依托单位: École Polytechnique de Montréal
• 依托单位国家: 加拿大
• 项目类别: Collaborative Research and Development Grants
• 财政年份: 2015
• 资助国家: 加拿大
• 起止时间: 2015-01-01 至 2016-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=576630
• 关键词: Plasma; actuation; improved; aircraft; aerodynamics

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.

这项研究计划是机械工程系研究人员之间的合作， 蒙特利尔理工学院和印度航空航天研究所航空航天工程系 坎普尔技术学院。它包括三个项目，涉及使用等离子体执行器的流量控制。流 控制包括在战略位置放置相对低功率的致动器， 对流场的影响等离子体致动器是一种新近的电流体技术，其能够将等离子体致动器转换成等离子体。 电能直接转化为流动动量，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（但以非常低的功率）， 介电材料。这种固态的、轻的、薄的、简单的纯电动致动器具有高带宽， 易于集成，从而提供了流量控制的首次实际广泛应用， 飞机空气动力学 研究的第一个项目旨在延迟飞机表面层流-湍流边界层转捩 用等离子体作动器来减少粘性阻力。第二个项目将调查 在大迎角时翼型上的附面层分离，以提高翼型襟翼在大迎角时的效率; 短期内，并最终取消襟翼，缝翼和扰流板完全。第三个项目是发展 两个新的概念，以改变升力的机翼和尾翼在小迎角与良好的重视边界 层通过修改翼尖涡和trainling边缘流动曲率与等离子体激励器， 消除所有可移动的飞行控制面。 蒙特利尔理工学院将负责建立和执行所有风洞验证 实验在所有三个项目以及一些数值模拟在项目3，而IIT-K将 负责项目1和2的所有计算工作以及项目3的部分工作。