This paper presents the results of tests conducted in the N.A.C.A. full-scale wind tunnel on a Fairchild F-22 airplane equipped with a special wing having split trailing-edge flaps. The flaps extended over the outer 90 percent of the wing span, and were of the fixed-hinge type having a width equal to 20 percent of the wing chord. The results show that with a flap setting of 59 degrees the maximum lift of the wing was increased 42 percent, and that the 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.
The Effect of Split Trailing-edge Wing Flaps on the Aerodynamic Characteristics of a Parasol Monoplane
1933-11-01
Sonstige
Keine Angabe
Englisch
AIRPLANES - FAIRCHILD 22 WIND TUNNEL TESTS(NACA FULL SCALE) , GLIDING ANGLE - MONOPLANES - EFFECT OF SPLIT WING FLAPS , MONOPLANES, PARASOL - EFFECT OF WING FLAPS , WINGS, HIGH LIFT , WING FLAPS - ZAP SPLIT , TAKE-OFF & LANDING - EFFECT OF WING FLAPS , WINGS FLAPS, SPLIT - FULL SPAN , AILERONS, UPPER-SURFACE
Engineering Index Backfile | 1931
Flight tests on wing sections using the parasol monoplane
TIBKAT | 1938
|The Lublin R.X. Parasol Monoplane
Emerald Group Publishing | 1929