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Experimental investigation of shock manipulation by the use of trailing edge brushes on a supercritical airfoil at transonic speeds

在跨音速超临界翼型上使用后缘刷进行冲击操纵的实验研究

基本信息

批准号：
239764064
负责人：
Professor Dr.-Ing. Herbert Olivier
金额：
--
依托单位：
Lehrgebiet und Abteilung für Hochtemperatur-Gasdynamik, Stoßwellenlabor (SWL)
依托单位国家：
德国
项目类别：
Research Grants
财政年份：
2013
资助国家：
德国
起止时间：
2012-12-31 至 2018-12-31
项目状态：
已结题

来源：
https://gepris.dfg.de/gepris/projekt/239764064?language=en
关键词：
Experimental investigation shock manipulation use

项目摘要

Throughout the project the degradation of upstream moving pressure waves by the use of trailing edge brushes and their effect on the transonic flow around the supercritical BAC 3-11 airfoil is investigated. The influence of the waves on the formation of the shock is of special interest. Previous schlieren pictures indicate that the bunching of pressure waves is involved in the formation of the shock. The results of preliminary experiments support the theory that the trailing edge brushes can delay the shock formation to higher Mach numbers.Within the single working packages the wave behavior itself will be analyzed, the most effective brush parameters will be defined as well as the overall influence of the waves and the brushes on the airfoil aerodynamics will be deduced. Therefore the diameter and length of the brush, the Mach number and the angle of attack will be systematically varied. Hence empirical design specifications for the brush will be established.Additional experiments will be done in the trisonic wind tunnel at the Institute of Aerodynamics at RTWH Aachen University to validate the results and to make sure there were no influences of wind tunnel interference in the Transonic Shock Tube (STK).The results will be implemented in a physical model of the wave movement based on equations for pressure waves over an oscillating airfoil. Finally there will be the possibility to transfer the design standards of the trailing edge brush and the physical model of the wave movement via similarity rules to real flight conditions.

在整个项目中，研究了使用后缘刷对上游移动压力波的退化及其对超临界BAC 3-11翼型跨音速绕流的影响。波对激波形成的影响是特别令人感兴趣的。以前的纹影照片表明，压力波的聚束参与了激波的形成。初步实验结果支持后缘刷可以延迟激波形成到更高马赫数的理论。在单个工作包中，将分析波的特性，确定最有效的刷参数，并推导出波和刷对翼型空气动力学的总体影响。因此，刷的直径和长度、马赫数和攻角将系统地变化。因此，将建立刷的经验设计规范。将在RTWH亚琛大学空气动力学研究所的三音速风洞中进行额外的实验，以验证结果，并确保跨音速激波管（STK）中没有风洞干扰的影响结果将在基于振荡翼型上的压力波方程的波运动的物理模型中实现。最后，将有可能通过相似性规则将后缘刷的设计标准和波浪运动的物理模型转换为真实的飞行条件。