Force Measurements and Computational Validation of a Transonic Wing-Tip Flow

Grisham James R.; Werling Michael G. Jr.; Braun Eric M.; Lu Frank K.

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Force Measurements and Computational Validation of a Transonic Wing-Tip Flow

机译：跨音速翼尖流的力测量和计算验证

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A NACA 0012 wing tip was tested at Mach 0.75 and chord Reynolds number of 3 million at incidences from -4 to 7deg in a transonic Ludwieg tube. The Mach and Reynolds numbers are representative of full-scale rotorcraft blades. Because of the short test time of 0.1s and high impulse loads, a dynamic calibration was applied to a conventional sidewall force balance to compensate for stress waves propagating within the force balance and test article. Numerical simulations of the entire test section were accomplished to provide data for comparison. The compensated, experimental lift and drag data compared well with the numerical results. This suggests that dynamic calibration improved the experimental data. This comparison demonstrates the feasibility of using complex models for calibrating short-duration wind tunnels in concert with numerical simulation.

机译：在跨音速的Ludwieg管中，NACA 0012翼尖的测试速度为0.75马赫，弦雷诺数为300万，入射角为-4至7度。马赫数和雷诺数代表全尺寸旋翼机叶片。由于0.1s的测试时间短且脉冲负载高，因此将动态校准应用于常规的侧壁力平衡，以补偿在力平衡和测试物品内传播的应力波。完成了整个测试部分的数值模拟，以提供数据进行比较。补偿后的实验升力和阻力数据与数值结果进行了比较。这表明动态校准改善了实验数据。该比较表明，结合数值模拟，可以使用复杂的模型来校准短时风洞。

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来源
《Journal of Aircraft》 |2016年第6期|1606-1613|共8页
作者
Grisham James R.; Werling Michael G. Jr.; Braun Eric M.; Lu Frank K.;
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作者单位

Univ Texas Arlington, Aerodynam Res Ctr, CFD Lab, Dept Mech & Aerosp Engn, Arlington, TX 76019 USA;

Univ Texas Arlington, Aerodynam Res Ctr, Dept Mech & Aerosp Engn, Arlington, TX 76019 USA|Solar Turbine, New Orleans, LA 70123 USA;

Univ Texas Arlington, Aerodynam Res Ctr, Dept Mech & Aerosp Engn, Arlington, TX 76019 USA|Boeing Co, Huntsville, AL 35808 USA;

Univ Texas Arlington, Aerodynam Res Ctr, Dept Mech & Aerosp Engn, Arlington, TX 76019 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);
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正文语种 eng
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Force Measurements and Computational Validation of a Transonic Wing-Tip Flow

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