Conceptual aircraft design with hybrid laminar flow control

摘要

This paper describes a methodology for conceptual design and optimization of aircraft with hybrid laminar flow control (HLFC) systems integrated into wing and tails. An existing conceptual aircraft design platform is enhanced by the necessary methods for sizing of HLFC system architecture and prediction of aerodynamic drag polars. These include transonic drag characteristics as well as transition prediction by analysing boundary layer instability mechanisms. The implemented methods are described and its sensitivities against relevant aircraft design parameters are discussed. The integrated sizing methodology allows to assess the net benefit of HLFC system integration on overall aircraft level and to minimize aircraft fuel consumption by variation of aircraft design parameters, cruise conditions and HLFC system parameters. To demonstrate the applicability of the developed methodology in conceptual aircraft design it is used for design and assessment of an HLFC long-range passenger aircraft. The influence of the HLFC main drivers Mach number and wing sweep angle on aerodynamics, systems and aircraft design characteristics is investigated. Further, aircraft component resizing is analysed to further exploit the fuel reduction potential of the HLFC technology.