Technical Memorandum of National Aerospace Laboratory
巻
615
ページ
48
発行年
1989-11
抄録（英）
Two-dimensional transonic wind tunnel tests of thin airfoils were made as a part of aerodynamic research on propeller blades for advanced turboprop engines. The test airfoils were NACA-16-202 and NACA16-204 which were developed as airfoils for conventional propeller systems at NACA in 1934. The Reynolds number is 8×106. The Mach number was varied from 0.6 to 1.0 and angles of attack from -10 to +16. In addition, vibration characteristics were measured and analyzed.
Investigation of ATP blades(PartI): Test of Thin Airfoils in the NAL 2-D Transonic Wind Tunnel
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