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Investigation in the Langley 19-foot Pressure Tunnel of Two Wings of NACA 65-210 and 64-210 Airfoil Sections with Various Type Flaps
James C. Sivells
Stanley H. Spooner
出版
National Advisory Committee for Aeronautics
, 1948
URL
http://books.google.com.hk/books?id=U7OolkIDnikC&hl=&source=gbs_api
EBook
FULL_PUBLIC_DOMAIN
註釋
An investigation has been conducted in the Langley 19-foot pressure tunnel to determine the maximum lift and stalling characteristics of two thin wings equipped with several types of flaps. Split, single slotted, and double slotted flaps were tested on one wing which had NACA 65-210 airfoil sections and split and double slotted flaps were tested on the other, which had NACA 64-210 airfoil sections. Both wings had zero sweep, an aspect ratio of 9, and a ratio of root to tip chord of 2.5. Wings were tested with and without a representative fuselage and with and without leading-edge roughness.
