Multidisciplinary Optimization of a Generic 2D High-Lift Configuration Regarding Kinematics, Aerodynamics and Flight Mechanics

This work deals with the multidisciplinary optimization of a generic two dimensional three element high-lift configuration. The objective of this work is to conduct a proof-of concept optimization and to find an optimized high-lift system with a feasible flap mechanism and enhanced aerodynamic performance which is reflected in a decreased take-off and landing distance. During the multidisciplinary optimization following disciplines are analyzed: Kinematics, Aerodynamics and Flight Mechanics. The proof-of-concept optimization is performed successfully and reveals a configuration with improved aerodynamic performance, reduced take-off and landing distance while the kinematic and aerodynamic constraints are satisfied. The overall take-off distance is reduced due to the augmentation of the maximum lift coefficient for the take-off configuration which leads to a significant shorter ground roll distance. At landing the moderate reduction in the overall landing distance is related to the enhanced maximum lift coefficient, which lowers the approach and touch-down speed. According to the data sets of the optimization it seems that the take-off and landing distance that form the objective function are not in conflict in this scenario. The optimization results indicate that the aerodynamic performance is more sensitive to parameters that define the slat setting and the magnitude of the flap deployment than to parameters that define the geometry of the flap mechanism