Unsteady Aerodynamic Model Based on the Leading-Edge Stagnation Point

Suryakumar Vishvas S.; Babbar Yogesh; Strganac Thomas W.; Mangalam Arun S.

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Unsteady Aerodynamic Model Based on the Leading-Edge Stagnation Point

机译：基于前沿停滞点的非定常气动模型

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The significance of the leading-edge stagnation point as an unsteady aerodynamic observable is investigated. Using first-order unsteady potential flow theory, a simple model relating the stagnation point to the unsteady lift is derived for an airfoil undergoing arbitrary unsteady maneuvers. In particular, the dynamic circulatory effects are shown to be accounted for by tracking the stagnation point. Linearization permits the superposition of solutions for thickness and camber. The model is validated using numerical simulations, employing both steady and unsteady panel methods. In addition, its validity is investigated experimentally through steady and unsteady wind-tunnel tests of a wing section. The stagnation point is estimated in real time from the convective heat transfer distribution measured using a hot-film sensor array instrumented around the wing's leading edge. Applications of these findings to flutter suppression and gust-load alleviation are experimentally demonstrated.

机译：研究了前沿停滞点作为非稳态空气动力学观测值的重要性。使用一阶非定常势流理论，推导了一个将停滞点与非定常升力相关联的简单模型，该模型针对经历了任意非定常操纵的机翼。特别地，动态循环效应显示为通过跟踪停滞点来解决。线性化可以叠加厚度和弯曲度的解决方案。该模型使用数值模拟进行了验证，采用了稳态和非稳态面板方法。此外，还通过机翼截面的稳态和非稳态风洞试验对它的有效性进行了实验研究。停滞点是根据对流传热分布实时估算的，该对流传热分布是使用安装在机翼前缘周围的热膜传感器阵列测得的。实验证明了这些发现在扑扑抑制和阵风减轻中的应用。

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来源
《Journal of Aircraft》 |2016年第6期|1626-1637|共12页
作者
Suryakumar Vishvas S.; Babbar Yogesh; Strganac Thomas W.; Mangalam Arun S.;
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作者单位

Texas A&M Univ, Dept Aerosp Engn, College Stn, TX 77843 USA;

Texas A&M Univ, Dept Aerosp Engn, College Stn, TX 77843 USA;

Texas A&M Univ, Dept Aerosp Engn, College Stn, TX 77843 USA;

Tao Syst Integrat Inc, Hampton, VA 23666 USA;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
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Unsteady Aerodynamic Model Based on the Leading-Edge Stagnation Point

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