Development of active flow control methods utilizing steady and pulsed plasma actuators for low speed flight Reynolds numbers

利用稳定和脉冲等离子体致动器开发用于低速飞行雷诺数的主动流量控制方法

• 批准号: 209952577
• 负责人: Professor Dr.-Ing. Christian Oliver Paschereit
• 金额: --
• 依托单位: Fachgebiet Experimentelle Strömungsmechanik
• 依托单位国家: 德国
• 项目类别: Research Grants
• 财政年份: 2012
• 资助国家: 德国
• 起止时间: 2011-12-31 至 2013-12-31
• 项目状态: 已结题
• 来源: https://gepris.dfg.de/gepris/projekt/209952577?language=en
• 关键词: Development; active; flow; control; methods

This research project is an investigation of plasma actuators for active flow control (AFC) and separation control at Reynolds numbers relevant for application in aviation. Within the last decade, plasma actuators have been introduced as a promising technology to control flow in fluid mechanics and has been of growing interest since then. Over the last years it has been shown that using AFC technology, the wing performance, efficiency, aircraft control and stall behavior can be influenced positively. This project is a continuation of the ongoing AFC plasma actuator studies at TU Berlin. It focuses on Plasma Sheet Actuators (PSA) and is divided in three phases. The goal of phase 1 is to identify a plasma actuator design with maximized induced velocities and high momentum transfer at Re 1 000 000 . Therefore, different generic designs of plasma actuators and combinations of actuators will be investigated with a novel test device. To generate higher momentum PSA will be used instead of the well known Dielectric Barrier Discharge (DBD) actuator. In phase 2 the chosen actuator design will be optimized for its application at high freestream velocities. In wind tunnel tests and by means of force and optical measurement techniques, the flow characteristics will be analyzed. Based on these results, phase 3 will involve an investigation of a wing equipped with these actuators and tested in a wind tunnel. The goal is to enhance the performance and the behavior in the post stall regime in the range of high Reynolds numbers. It is expected that the PSA behaves superiorly to the DBD actuator, since a larger region is used to couple momentum into the fluid.

本研究项目是针对航空应用的主动流动控制(AFC)和雷诺数分离控制的等离子体致动器的研究。在过去的十年里，等离子体激励器被引入作为流体力学中一种很有前途的流动控制技术，并从那时起引起了越来越大的兴趣。过去几年的研究表明，使用AFC技术可以对机翼的性能、效率、飞机操纵和失速行为产生积极的影响。该项目是柏林理工大学正在进行的亚足联等离子体激励器研究的继续。它专注于等离子薄板致动器(PSA)，分为三个阶段。第一阶段的目标是确定一种在Re为1 000 000时具有最大诱导速度和高动量传递的等离子体激励器设计。因此，将利用一种新的测试装置来研究不同通用设计的等离子体致动器以及致动器的组合。为了产生更高的动量，将使用PSA来代替众所周知的介质阻挡放电(DBD)致动器。在第二阶段，所选的执行器设计将针对其在高自由流速度下的应用进行优化。在风洞试验中，借助于测力和光学测量技术，分析了流动特性。基于这些结果，第三阶段将包括对配备了这些致动器的机翼进行调查，并在风洞中进行测试。其目标是在高雷诺数范围内改善失速后区域的性能和行为。预计PSA的性能优于DBD执行器，因为使用更大的区域来将动量耦合到流体中。