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The purpose of this study was to design and analyze an adaptive maximum-performance take-off system for use in any aircraft having critical take-off requirements. This was accomplished by using various combinations of available flight parameters as inputs to a flight director, analyzing each combination under conditions of normal and reduced aircraft thrust on an analog computer and selecting the combination giving the maximum take-off performance without any sacrifice of flight safety. This preliminary investigation revealed that a system holding a constant angle-of-attack until acceleration goes to zero, and then holding a constant velocity, produced maximum take-off performance. To insure its dynamic response the selected system was then analyzed for stability by the root-locus technique and then further sensitized on the analog computer. This analysis of the system indicated that the compensatory effects of Ã¿ and Â¿ were required to furnish the necessary lead to the system. The compensated system was then instrumented to drive a commercially available indicator and installed and flown in an Air Force T-37 flight simulator where the indicator take-off performance was compared with that of a normal take-off. The results indicated that a substantial increase in performance over the normal take-off techniques can be obtained for modern civilian and military aircraft having critical take-off requirements. Not only can the take-off performance obtained from these aircraft be improved, but safety can also be increased. The use of the flight director made complete pitch control possible with only one instruments.