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The Effect of Split Trailing-edge Wing Flaps on the Aerodynamic Characteristics of a Parasol Monoplane

出版	National Advisory Committee for Aeronautics, 1933
URL	http://books.google.com.hk/books?id=eCFRNAAACAAJ&hl=&source=gbs_api

註釋The results show that with a flap setting of 59 degrees the maximum lift of the wing was increased 42 percent, and that flaps increased the range of available gliding angles from 2.7 degrees to 7.0 degrees. Deflection of the split flaps did not increase the stalling angle or seriously affect the longitudinal balance of the airplane. With flaps down the landing speed of the airplane is decreased, but the calculated climb and level-flight performance is inferior to that with the normal wing. Calculations indicate that the take-off distance required to clear an obstacle 100 feet high is not affected by flap settings from 0 degrees to 20 degrees but is greatly increased by larger flap angles.