Shock Tube Study of the Flow past Circular-Arc Airfoils Using a Mach-Zehnder Interferometer

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概要

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• Interferometer measurements are given of pressure distributions of circular-arc airfoils with thickness ratios 10%, 15%, 20% at angles of attack 0°, 1.6°, 3.2°, 4.8°, 6.4° in the flow of Mach numbers 0.75, 0.85, 0.95, 1.03, 1.1, 1.2, 1.3, 1.4, 1.55, 1.7 1.9 with Reynolds numbers based on chord length 2.2〜1.9×10^5. From these data, drag coeffcients, lift coefficients and pitching moment coefficients were calculated for each case. These coefficients and lift-angle of attack curves are in good agreement with transonic similarity law. Results are also compared with other wind tunnel experiments.

• 社団法人日本物理学会の論文
• 1955-07-05

著者

• Oshima Koichi

  Institute Of Science And Technology University Of Tokyo

• Oshima Koichi

  Institute Of Industrial Science University Of Tokyo

関連論文

• Shock Tube Study of the Flow past Circular-Arc Airfoils Using a Mach-Zehnder Interferometer
• Experiments on the Cylindrical Blast Waves
• Experimental Studies of the Interaction of a Plane Shock Wave with a Circular Cylinder

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