摘要: The test objective was to evaluate the performance and flying qualities of the F-4E aircraft equipped with the two-position leading edge slat and to obtain data necessary to update the F-4 Flight Manual. The two-position slat test... 展开 The test objective was to evaluate the performance and flying qualities of the F-4E aircraft equipped with the two-position leading edge slat and to obtain data necessary to update the F-4 Flight Manual. The two-position slat test results show an increase in turning capability in most of the flight envelope compared with that of the basic F-4E. The normal takeoff rotation technique described in the Flight Manual was considered unsatisfactory for slat-equipped aircraft. The installation of the two-position wing leading edge slat has degraded the maximum speed capability of the F-4 aircraft slightly. Cruise data obtained during the tests show a degradation in cruise performance of approximately four percent for the retracted slat configuration and seven percent for the extended slat. Decreased static stability made precise control of angle of attack(AOA) moderately difficult during landing approaches at 19 units AOA. Rudder rolls performed at high AOA showed improved performance. Lateral-directional flying qualities in the power approach configuration were generally not as good as with the unslatted F-4E, but were satisfactory. Tests performed to evaluate the flying qualities with simulated failures in one or more slat actuators revealed minor, acceptable degradations from the flying qualities observed with the symmetric slat condition. 收起