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首页> 外文会议>AHS Specialists Conference on Aeromechanics Design for Transformative Vertical Flight >Correlation of Predictions with Measured Pressure Data from a Slowed Mach-Scaled Rotor at High Advance Ratios
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Correlation of Predictions with Measured Pressure Data from a Slowed Mach-Scaled Rotor at High Advance Ratios

机译：在高预远比率下从慢速的Mach-Scaled转子与测量压力数据的相关性的相关性

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摘要

Slowing down the rotor in forward flight to reduce the rotor tip speed is proved to be a viable means of expanding the cruise speed limitation of a compound helicopter. However, in a high advance ratio flight regime, many aerodynamic phenomena remain unclear, especially in the reverse flow region. To investigate the aerodynamic phenomena in high advance ratio flight regimes and validate the advanced design tools, a series of wind tunnel tests were conducted progressively with a slowed Mach-scaled articulated rotor in the Glenn L. Martin Wind Tunnel. In the 2016 wind tunnel test, enough pressure data from blade embedded sensor ports were obtained to determine integrated sectional airload at 30% radius. The experimental results of rotor performance, control angle, blade airload and surface pressure, and blade structural load were compared with the predictions of comprehensive analysis for prescribed-motion CFD study and CFD/CSD coupled study. The rotor performance and control angle correlation studies were mainly done with comprehensive analysis. The predictions were satisfactory for most cases, but degrades with increasing advance ratio. The blade surface pressure, airload and structural load correlation studies were carried out with CFD/CSD coupled predictions at a representative high advance ratio and high collective case. The data correlation is very good, especially for sectional normal force and pitching moment.
机译：被证明，向前飞行转移转移以减小转子尖端速度是扩展复合直升机的巡航限制的可行方法。然而，在高级比率方面，许多空气动力学现象仍然不清楚，特别是在逆流区域中。为了调查高级比率方案的空气动力学现象并验证先进的设计工具，一系列风洞试验是通过Glenn L. Martin风洞的速度慢的马克铰接式转子进行逐步进行。在2016年风洞测试中，获得了来自刀片嵌入式传感器端口的足够压力数据以确定综合截面飞程以30％半径。与规定运动CFD研究和CFD / CSD耦合研究的综合分析预测进行了比较转子性能，控制角，叶片空气载体和表面压力的实验结果，以及叶片结构载荷。转子性能和控制角相关研究主要通过综合分析进行。对于大多数情况而言，预测是令人满意的，但随着提前比率的增加而劣化。用CFD / CSD耦合预测以代表性高预先比率和高集体壳体进行叶片表面压力，空降和结构载荷相关研究。数据相关性非常好，特别是对于截面正常力和俯仰力矩。

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