摘要: This document presents stability and control derivatives for the F-4E aircraft which were extracted from flight test data using several data reduction techniques. Data reduction methods gave realistic results but the quality of th... 展开 This document presents stability and control derivatives for the F-4E aircraft which were extracted from flight test data using several data reduction techniques. Data reduction methods gave realistic results but the quality of the results could be improved. Flight test results were compared with available wind tunnel predictions. Flight test results differed significantly from the wind tunnel data by showing a strong noseup pitching moment when accelerating through the transonic region, positive directional stability over the sideslip range was encountered during wing rock at high angles of attack, and large adverse yaw due to aileron deflection at high angles of attack. (Author) 收起