The invention provides a full-seam flap lift-augmentation and drag-reduction system and a construction method thereof.The system is arranged on the two sides of an aircraft fuselage and comprises a basic wing and a full-seam flap, the basic wing adopts a laminar flow wing section with the large relative thickness, the full-seam flap is arranged above the basic wing and close to the upper wing surface of the basic wing, and a gap is formed between the full-seam flap and the upper wing surface; the full-seam flap covers the whole wingspan length of the upper wing face in the spanwise direction, and the curvature of the full-seam flap is the same as that of the upper wing face. According to the method, lift augmentation and drag reduction schemes of the wings are comprehensively considered, drag reduction equipment is developed and designed while a lift augmentation system is constructed, lift force and drag are optimized at the same time, and therefore a large lift-drag ratio is obtained, the flight efficiency is improved, energy (oil or electricity) is saved, and an aircraft can fly faster and farther and stay in the air for a longer time; the skating distance is shorter, a large amount of land resources are saved, and energy-saving, emission-reducing, low-carbon and green travel is realized; and the structure is simple and reasonable, cost is low, and application and popularization are facilitated.
本发明提供一种全缝襟翼增升减阻系统及其构建方法,系统设置在飞行器机身的两侧,包括基础机翼、全缝襟翼,基础机翼采用相对厚度大的层流翼型,全缝襟翼设置在基础机翼的上方,靠近基础机翼的上翼面,与上翼面之间具有间隙;全缝襟翼的展向遮覆上翼面的全部翼展长度,全缝襟翼的曲率与上翼面的曲率相同。本发明综合考虑机翼的增升和减阻方案,在构建增升系统时同时开发设计减阻设备,同时优化升力和阻力,从而获得很大的升阻比,提升了飞行效率,有利于节省能源(省油或省电),使飞机飞得更快、更远,留空时间更长;使得滑跑距离更短,节约大量土地资源,实现节能、减排、低碳、绿色出行;并且结构简单、合理,成本较低,利于推广应用。
Full-seam flap lift augmentation and drag reduction system and construction method thereof
一种全缝襟翼增升减阻系统及其构建方法
2025-03-25
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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