Supercritical Airfoil Design for Future High-Altitude Long-Endurance Concepts

Kasim Biber; Carl P. Tilmann

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Supercritical Airfoil Design for Future High-Altitude Long-Endurance Concepts

机译：超临界机翼设计，为未来的高空长期耐力概念

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The design and analysis is presented of a new laminar flow airfoil for a future high-altitude long-endurance aircraft that has an operational condition at supercritical speeds. The XFOIL and MSES computational codes were used to design, modify, and analyze the airfoil. The airfoil has enough thickness and performance to meet the requirements set for one of the U.S. Air Force Research Laboratory's SensorCraft concepts: a joined-wing configuration with a diamond shape in planform and front views. This SensorCraft concept's geometry and operational altitudes and speeds were used to determine the airfoil design conditions. The airfoil has a drag bucket over a large range of lift coefficients. Boundary-layer transition location is at about 60% chord upper surface and 70% chord lower surface and is characterized by a laminar separation bubble, which decreases in size with increasing angle of attack. Sensitivity studies were carried out to investigate the effects of Reynolds number and Mach number, along with boundary-layer transition parameters. Further experimental work needs to be performed to validate the design.

机译：提出了一种新的层流翼型的设计和分析，该翼型是用于未来的高海拔长寿命飞机，该飞机在超临界速度下具有运行条件。 XFOIL和MSES计算代码用于设计，修改和分析机翼。机翼的厚度和性能足以满足美国空军研究实验室的SensorCraft概念之一的要求：在平面图和正视图中采用菱形的联合机翼构型。该SensorCraft概念的几何形状，运行高度和速度用于确定机翼设计条件。机翼具有在大升力系数范围内的拖斗。边界层过渡位置在弦上表面的大约60％和弦下表面的70％处，并具有层状分离气泡的特征，该气泡的尺寸随攻角的增加而减小。进行了敏感性研究，以研究雷诺数和马赫数以及边界层过渡参数的影响。需要进行进一步的实验工作以验证设计。

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来源
《Journal of Aircraft》 |2004年第1期|p.156-164|共9页
作者
Kasim Biber; Carl P. Tilmann;
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作者单位

Istanbul Technical University, 34870 Istanbul, Turkey;

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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
中图分类航空;
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Supercritical Airfoil Design for Future High-Altitude Long-Endurance Concepts

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