Flat-plate flaps with no wing cutouts and flaps having Clark Y sections with corresponding cutouts made in wing were tested for various flap deflections, chordwise locations, and gaps between flaps and airfoil contour. The drag was slightly lower for wing with airfoil section flaps. Satisfactory aileron effectiveness was obtained with flap gap of 20% wing chord and flap- nose location of 80% wing chord behind leading edge. Airflow was smooth and buffeting negligible.
Wind-Tunnel Investigation of a Rectangular NACA 2212 Airfoil with Semi- span Ailerons and with Nonperforated, Balanced Double Split Flaps For Use as Aerodynamic Brakes
1945
76 pages
Report
No indication
English
Engineering Index Backfile | 1941
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