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Investigations of a Spoiler-type Lateral Control System on a Wing with Full-span Flaps in the Langley 19-foot Pressure Tunnel

出版	National Advisory Committee for Aeronautics, 1947
URL	http://books.google.com.hk/books?id=Why8YgEACAAJ&hl=&source=gbs_api

註釋Tests of a partial-span model of a large bomber-type airplane were conducted to determine the aerodynamic characteristics of the wing equipped with full-span flaps and a retractable spoiler and aileron lateral control systems. The arrangement consisted of (1) a double slotted flap extending over approximately 86 percent of the wing semispan, (2) a 20-percent constant-percentage-chord aileron extending from the outboard endo of the flap of teh wing tip, and (3) a retractable spoiler, located at the 65-percent of the wing station and extending from approximately 63 percent of the wing semispan to the wing tip. In addition, tests were made of a wing vent (of 1 and 2 percent of the wing chord located directly behind the spoiler), perforations in the spoiler, a slot or cut-out along the lower edge of the spoiler, and spoilers of various spans.