科研之友
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摘要
This study uses multidisciplinary design optimization to explore strut-braced and truss-braced wing configurations in enhancing the performance of medium-range transonic transport aircraft. The truss- and strut-braced wing concepts synergize structures and aerodynamics to decrease weight and drag. Past studies have found that these configurations can achieve significant performance benefits compared to a cantilever aircraft with a Mach 0.85, long-range Boeing 777-200ER-like mission. The objective of this study was to explore these benefits applied to a medium-range Boeing 737-800NG-like aircraft. Results demonstrate the significant performance benefits of the strut-braced and truss-braced wing configurations. Configurations are also optimized for 1990s or advanced-technology aerodynamics. For the 1990s aerodynamic-technology minimum-takeoff-gross-weight cases, the strut-braced and truss-braced wing configurations achieve reductions in the takeoff gross weight of as much as 6% with 20% less fuel weight than the comparable cantilever configurations. The 1990s aerodynamic-technology minimum-fuel cases offer fuel-weight reductions of about 13% compared to the 1990s aerodynamic-technology minimum-takeoff-gross-weight configurations, and 11% when compared to the 1990s aerodynamic-technology minimum-fuel optimized cantilever configurations. The advanced aerodynamic-technology minimum-takeoff-gross-weight configurations feature an additional 4% weight savings over the comparable 1990s aerodynamic-technology results, while the advanced aerodynamic-technology minimum-fuel cases show fuel savings of 12% over the 1990s aerodynamic-technology minimum-fuel results. This translates to a 15% reduction in takeoff gross weight for the advanced-technology minimum-takeoff-gross-weight cases, and a 47% reduction in fuel consumption for the advanced-technology minimum-fuel cases when compared to the simulated Boeing 737-800NG.
- 出版日期2012-12
