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，研究了上游运动压力波的降解，并研究了它们对超临界BAC 3-11翼型围绕的跨气流的影响。波浪对冲击形成的影响是特别感兴趣的。先前的Schlieren图片表明，压力波的束涉及冲击的形成。初步实验的结果支持了这样的理论：后缘刷子可以将冲击形成延迟到更高的马赫数。在单个工作包中，将分析波行为本身，将定义最有效的刷子参数，以及波浪和刷子对机翼空气动力学的总体影响。因此，刷子的直径和长度，马赫数和攻击角将系统变化。因此，将确定刷子的经验设计规范。在RTWH Aachen大学的空气动力学研究所的三角风隧道中，将进行无限的实验，以验证结果，以确保在跨性别冲击管（STK）中没有风力隧道干扰的影响（STK）（STK）。在物理模型中，在浪潮中实现了潮流的效果。最后，有可能通过相似性规则与真实飞行条件传输后边缘刷的设计标准和波动的物理模型。