Optimization of Non-Planar Wing Aircraft Configurations

Abstract

Air traffic is expected to grow over the next few decades, which will cause the global fuel consumption to increase. Reducing the drag of an aircraft will result in a reduction of the fuel consumption. Non-planar configurations may offer a solution to reduce the drag while maintaining the performance of today’s aircraft. The aim of this study is to identify the effect of using different climb and descent strategies on the planform optimization of non-planar wing configurations. In order to analyze these effects, a generic aero-structural model is developed, which combines a developed mission analysis model to assess the aircrafts performance over an entire mission profile. In this study, four aircraft configurations are considered: a planar configuration, a wing with winglet configuration, a C-wing configuration, and a box wing configuration. Using a gradient based optimization method, the configurations are optimized for minimum fuel consumption over an entire mission profile. The optimized box wing configuration offer fuel reductions up to 2% with respect to the planar configuration. The lift over drag ratio of the box wing is lower, but this is compensated for by its lighter wing mass. The C-wing has higher lift over drag ratios, but this does not compensate for the heavier wing mass. Therefore the C-wing results in a higher fuel consumption.