Flow Visualization around Double Wedge Airfoil by Focusing Schlieren System with Rod Extended Light Source
Flow Visualization around Double Wedge Airfoil by Focusing Schlieren System with Rod Extended Light Source
复制标题
通过带杆延伸光源的聚焦纹影系统实现双楔翼型周围的流动可视化
DOI：
10.3154/tvsj.27.113
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发表时间：
2007
期刊：
影响因子：
--
通讯作者：
H. Kitano
中科院分区：
文献类型：
--
作者：
M. Kashitani;Y. Yamaguchi;Takeshi Suda;H. Kitano
113 * 原稿受付 2007 年 7 月 26 日 1) 正会員 防衛大学校 航空宇宙工学科(〒239-8686 神奈川県横 須賀市走水 1-10-20, Email : kasitani@cc.nda.ac.jp) 2) 正会員 防衛大学校 航空宇宙工学科 3) 防衛大学校 理工学研究科 ロッド拡散光源を有するフォーカシングシュリーレン装置 による二重くさび翼型まわりの観察 樫谷賢士 1),山口裕 2),須田武志 3),北野秀樹 3) Flow Visualization around Double Wedge Airfoil by Focusing Schlieren System with Rod Extended Light Source Masashi KASHITANI, Yutaka YAMAGUCHI, Takeshi SUDA and Hideki KITANO ABSTRACT In the present study, we adopt a rod lighting system to the focusing schlieren system to obtain the higher and more uniform bright lighting at the test section. And flow visualization around a double wedge airfoil was performed in the transonic shock tube flow by using the focusing schlieren system. The span, chord length and maximum thickness of the model are 60mm, 75mm and 7.5mm, respectively. The hot gas Mach numbers (test Mach numbers) are from 0.80 to 0.86, and the Reynolds numbers are from 4.0×105 to 4.6×105. The test results show that an increment of light intensity was obtained by the experiments of the rod extended light source, and relatively constant light intensity was achieved at the test plane surface, and that, on the shock tube airfoil testing at the angle of attack 0°, if the Mach number is increased, the shock wave on the airfoil model moves to further downstream. This latter result is nearly the same as aerodynamic characteristics of NACA0012 airfoil model.