Design of a high-lift, thick airfoil for unmanned aerial vehicle applications

被引：0
|
作者：
Cerra, David F. [1 ,2 ]
Katz, Joseph [1 ,2 ]
机构：
[1] San Diego State University, San Diego, CA 92182, United States
[2] Department of Aerospace Engineering and Engineering Mechanics
来源：
Journal of Aircraft | 1600年 / 45卷 / 05期
关键词：
The aerodynamic design of high-altitude unmanned aerial vehicles is driven by the rapidly decreasing air density at the upper boundaries of the atmosphere. A corresponding increase in wing area cannot provide a simple solution because of the additional weight and flexibility of the high-aspect-ratio wings. The excessive spanwise flexibility can be addressed by developing thicker airfoil sections that will increase the wing bending stiffness. Additional reduction in the expected wing size could be achieved by increasing the design cruise lift coefficient. Consequently; the objective of this study was to develop a 24% thick; two-element airfoil section capable of lift coefficients approaching two. Expected operational Reynolds number was estimated within the range of 0.5 to 1.0 × 106. A secondary objective of this study was to experiment with the airfoil design-optimization procedure; which later could be automated;
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摘要：
Journal article (JA)
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页码：1789 / 1793
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