The invention discloses a fixed hinge type flap design structure of an NASA MS (1)-0317 airfoil profile, which is characterized in that on the basis of the NASA MS (1)-0317 airfoil profile, the relative chord length of a flap is designed to be 29%, and the relative deflection of a fixed hinge of the flap is designed to be 15%; the relative radius of the front edge of the flap is designed to be 6%, and the relative thickness of the flap is designed to be 22%; the horizontal length of the flap cabin in the chord line direction of the airfoil profile is designed to be 12% of the chord length of the airfoil profile, and the trailing edge angle of the flap cabin is designed to be 5 degrees; the maximum designed flap skewness is 25 degrees, the designed flap gap width is 1.4% of the wing section chord length, and the designed flap gap overlapping amount is 4.5% of the wing section chord length. The flap has the advantages of being simple in flap unfolding mechanism, light in weight and good in reliability and maintainability, the pneumatic lift augmentation capacity of the flap meets the design requirement of a conventional general aircraft, and the flap is excellent in comprehensive performance.
本发明公开了一种NASA MS(1)‑0317翼型的固定铰链式襟翼设计结构,包括:在NASA MS(1)‑0317翼型的基础上,襟翼相对弦长设计为29%,襟翼的固定铰链相对下沉量设计为15%;襟翼前缘相对半径设计为6%、襟翼相对厚度设计为22%;襟翼舱在翼型弦线方向的水平长度设计为12%翼型弦长、襟翼舱后缘角设计为5°;最大设计襟翼偏度为25°,设计襟翼缝道宽度为1.4%翼型弦长,设计襟翼缝道重叠量为4.5%翼型弦长。本发明具有襟翼展开机构简单、重量轻、可靠性和维护性好的优点,并且其气动增升能力也满足常规通用飞机的设计需求,是一款综合性能较优的襟翼。
Fixed hinge type flap design structure of NASA MS (1)-0317 airfoil profile
NASA MS(1)-0317翼型的固定铰链式襟翼设计结构
2024-02-02
Patent
Electronic Resource
Chinese
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