Design and predictions for high-altitude (low Reynolds number) aerodynamic flight experiment
Design and predictions for high-altitude (low Reynolds number) aerodynamic flight experiment
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DOI：
10.2514/2.2652
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发表时间：
1999-07
影响因子：
2.2
通讯作者：
Donald Greer;Philip J. Hamory;Keith Krake;M. Drela
中科院分区：
文献类型：
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作者：
Donald Greer;Philip J. Hamory;Keith Krake;M. Drela
Donald Greer* 和 Phil Hamory *NASA Dryden 飞行研究中心，爱德华兹，加利福尼亚州 93523Keith Krake)Sparta, Inc.，爱德华兹，加利福尼亚州 93523 和 Mark Drela！麻省理工学院，剑桥，马萨诸塞州 02139 NASA Dryden 飞行研究中心正在开发的滑翔机将支持高空飞行实验。该实验将测量机翼在高海拔（70,000-100,000 It）、低雷诺数（2 × los-7 × 10s）和高亚音速马赫数（0.5和0.65）下的性能参数。翼型截面升力和阻力由皮托管和静压测量确定。分离气泡的位置、Tollmien--Schlichting 边界层不稳定频率和涡流脱落是从热胶片上测量的。介绍了计划飞行实验的细节以及翼型性能的几个预测
Donald Greer* and Phil Hamory *NASA Dryden Flight Research Center, Edwards, California 93523Keith Krake )Sparta, Inc., Edwards, California 93523andMark Drela !Massachusetts Institute of Technology, Cambridge, Massachusetts 02139A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experi-ment. The experiment will measure the performance parameters of an airfoil at high altitudes (70,000-100,000 It),low Reynolds numbers (2 × los-7 × 10s), and high subsonic Mach numbers (0.5 and 0.65). The airfoil section liftand drag are determined from pitot and static pressure measurements. The locations of the separation bubble,Tollmien--Schlichting boundary-layer instability frequencies, and vortex shedding are measured from a hot-filmstrip. The details of the planned flight experiment are presented as well as several predictions of the airfoil perfor-