A Technique for Shortening Landing Run Distance of an Aircraft by Symmetrical Deflection of Split Elevator and Rudder
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In this work, we investigate an application of symmetrical deflection of the split elevators and rudder up to 45 degrees to function as air-brakes during landing run for shortening its distance. A computational analysis for the landing run under standard atmospheric conditions is conducted. The effect of the proposed solution on the aircraft structure and performance was studied.
Keywordslanding run shortening takeoff and landing performance elevator rudder
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