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Active Control for Transition Delay of Two Dimensional Boundary Layers in In-Flight Experiments

飞行实验中二维边界层跃迁延迟的主动控制

基本信息

批准号：
247294283
负责人：
Professor Dr.-Ing. Sven Grundmann
金额：
--
依托单位：
Lehrstuhl Strömungsmechanik
依托单位国家：
德国
项目类别：
Research Grants
财政年份：
2014
资助国家：
德国
起止时间：
2013-12-31 至 2019-12-31
项目状态：
已结题

来源：
https://gepris.dfg.de/gepris/projekt/247294283?language=en
关键词：
Active Control Transition Delay Two

项目摘要

Reduction of skin friction on aircraft remains an economic and environmental issue of importance; however, active methods to achieve such reductions still require significant research and development efforts to reach industrial maturity. Even very basic questions regarding the most appropriate concept, actuator or the achievable efficiency are still open for discussion. It is within this context that the present project proposes the application of plasma actuators to invoke transition delay in two-dimensional boundary layers, in the laboratory, but especially in-flight. Previous studies have demonstrated two basic principles for achieving transition delay; a stabilization of the boundary layer, and the active wave cancellation, which have been used in four different operating modes. Many of these precursor experiments have been conducted in simple wind tunnel experiments; however also very elaborate and intricate in-flight campaigns with the institute's motorized gliders have demonstrated delay of naturally occurring transition. This very extensive preliminary work underlines the enormous potential of plasma actuators for active control on aircraft.The proposed work program intricately interweaves theoretical, numerical and experimental studies of generic configurations of flat plates and wing profiles in wind tunnels with experiments under realistic conditions on aircraft. Numerical solutions of the boundary-layer equations, together with the experimentally determined body force invoked by the plasma actuators, allow a theoretical stability analysis to assist in configuring actuator systems and arrays for energy efficient transition delay. This up-front design and optimization is then to be verified and improved using flat plate experiments in wind tunnels. Subsequent wind tunnel experiments on a full-scale wing glove can then be directly followed by in-flight experiments. Novel approaches for analyzing the power, effectiveness and induced forces of plasma actuators will then be used to evaluate the various operating modes in terms of energy balance, yielding estimates of overall efficiency. This is intended to provide a direct prognosis of how viable this application plasma actuation is in the future.

减少飞机的表面摩擦仍然是一个重要的经济和环境问题；然而，实现这种减少的积极方法仍然需要大量的研究和开发努力，才能达到工业成熟。即使是关于最合适的概念、执行器或可实现的效率的最基本的问题也仍有待讨论。正是在这一背景下，本项目建议在实验室中，特别是在飞行中，应用等离子体激励器来激发二维边界层中的过渡延迟。以前的研究已经证明了实现过渡延迟的两个基本原理：稳定边界层和有源波对消，这两个原理已经在四种不同的工作模式中使用。许多这些前驱实验都是在简单的风洞实验中进行的；然而，研究所的机动滑翔机在飞行中也进行了非常复杂和复杂的运动，证明了自然发生的过渡的延迟。这项非常广泛的前期工作突出了等离子体致动器在飞机主动控制方面的巨大潜力。拟议的工作计划将风洞中平板和翼型的一般构型的理论、数值和实验研究与飞机上实际条件下的实验错综复杂地交织在一起。边界层方程的数值解，以及由等离子体激励器所激发的实验确定的体力，允许进行理论稳定性分析，以帮助配置激励器系统和阵列以实现能量高效的过渡延迟。这种前期的设计和优化将通过风洞中的平板实验进行验证和改进。随后在全尺寸机翼手套上进行的风洞实验可以直接在飞行实验之后进行。然后，将使用分析等离子体致动器的功率、有效性和诱导力的新方法，从能量平衡的角度评估各种操作模式，从而得出总体效率的估计。这是为了提供对这种应用等离子体驱动在未来的可行性的直接预测。