Investigation of Model Wake Blockage Effects at High Angles of Attack in Low-Speed Wind Tunnel

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概要

• 論文の詳細を見る

• To improve the fidelity of measured aerodynamic characteristics at high angle of attack for modern jet fighters, this paper examines the model wake blockage effect. The wake blockage effect in a 2.2×3.1 m low-speed wind tunnel is investigated by analyzing drag and wall pressure measurements. Circular flat plates of different sizes are used to simulate a test model at high angles of attack. The present analysis results in simple formulas for corrections of model wake blockage effect. To verify the present correction formula, the NASA TP-1803 model is force-tested in the tunnel. The corrected test data agree well with the NASA TP-1803 data.

• 社団法人 日本航空宇宙学会の論文
• 2008-05-04

著者

• SHYU Lih-Shyng

  Department of Mechanical Engineering, National Chung-Hsing University

• CHUANG Shu-Hao

  Office of Research and Development, Chung Hwa University of Medical Technology

• Shyu Lih-shyng

  Department Of Mechanical Engineering National Chung-hsing University

• Chuang Shu-hao

  Dean Of R&d Division Chung Hwa University Of Medical Technology

関連論文

• Static and Dynamic Aerocharacteristics Testing of Strake-Wing Aerial Vehicle in Water Tunnel
• Investigation of Model Wake Blockage Effects at High Angles of Attack in Low-Speed Wind Tunnel
• Static and Dynamic Aerocharacteristics Testing of Advanced Stealth Aircraft in Water Tunnel

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