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EXPERIMENTAL AND NUMERICAL AERODYNAMIC INVESTIGATION OF ADVANCED TAIL BOOM DESIGNS BASED ON OPTIMIZED THICK AIRFOIL PROFILES

机译:基于优化厚翼型轮廓的先进尾翼设计的实验和数值气动研究

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The current paper aims at validating the aerodynamic performance of several advanced helicopter tail boom concepts answering to different aerodynamic optimization objectives. The flow solver validation has been carried out by comparing the numerical predictions with comprehensive measurement data obtained at the CNAM-IAT Wind Tunnel test facility. The comparison confirmed the accuracy and quality of the optimization results particularly in terms of ranking of the different optimal solutions. In this study, the database is further exploited to assess the capability of the CFD approach using the elsA solver to predict the aerodynamic characteristics of theses optimized shapes.
机译:本论文旨在验证几种先进的直升机尾架概念的空气动力学性能,以应对不同的空气动力学优化目标。通过将数值预测与CNAM-IAT风洞测试设施获得的综合测量数据进行比较,对流量求解器进行了验证。比较结果证实了优化结果的准确性和质量,特别是在不同优化解决方案的排名方面。在这项研究中,该数据库被进一步利用以评估使用elsA求解器的CFD方法预测这些优化形状的空气动力学特性的能力。

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