Flight tests were made of a Navy F2A-2 airplane specially equipped with. full-span NACA slotted flaps and with two sets of lateral controls: internally balanced, sealed ailerons on the flap trailing edge for use with flaps up 2nd slot-lip ailerons, immediately forward of the flaps, for use with flaps down. The tests , made with various flap positions ranging from neutral to 50 deg, included determination of effectiveness and stick forces of the two aileron systems, power-off maximum lift coefficients , and static longitudinal stability . The effectiveness of the trailing-edge ailerons was somewhat low, primarily became of lack of rigidity in the control system; the stick forces were fairly large, probably as a result of leakage through the aileron seal . The slot-lip ailerons were very effective, particularly at large flap deflections; with a slight modification of the control linkage, the stick-force characteristics would probably be satisfactory for all conditions under which these ailerons would be used, The highest maximum lift coefficient, which occurred at a flap deflection of about 40 deg, was 2.43. With the center of gravity at 30.4 percent of the mean aerodynamic chord and with engine idling, the airplane had positive static longitudinal stability for all conditions tested; with level flight power, the stability decreased with increasing flap deflection and the airplane became unstable for flap deflections of 4.0 deg and 50 deg at service indicated airspeeds below 100 miles per hour.


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    Title :

    Flight Tests of F2A-2 Airplane with Full-Span Slotted Flaps and Trailing-Edge and Slot-Lip Ailerons


    Contributors:

    Publication date :

    1943


    Size :

    46 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English