The invention discloses a high-performance airfoil profile suitable for active stability augmentation of a refueling taper sleeve, which is characterized in that the maximum relative thickness of the airfoil profile is set to be 5.6% under pneumatic/geometric constraint conditions, and the maximum relative thickness position is located at 10% of chord length; the maximum relative camber of the airfoil is set to be 4%, and the position of the maximum relative camber is located at 31% of the chord length; the radius of the relative leading edge of the airfoil profile is 0.0081, and the relative thickness of the trailing edge of the airfoil profile is 1%. According to the airfoil profile designed by the invention, the lift force can be kept linearly changed along with the attack angle within the range of the attack angle of 16 degrees under the conditions that the flight speed is 0.2 to 0.3 time of sound speed, the flight height is 1 thousand to 4 kilometers, and relatively large lift force is provided for the conical cup winglet, so that effective support can be provided for inhibiting the floating of the conical sleeve in the oil adding/receiving process.
本发明公开了一种适用于加油锥套主动增稳的高性能翼型,满足气动/几何约束条件下,设定翼型最大相对厚度为5.6%,最大相对厚度位置位于10%弦长;设定翼型最大相对弯度为4%,最大相对弯度位置位于31%弦长;设定翼型相对前缘半径为0.0081,翼型后缘相对厚度为1%。本发明所设计的翼型可实现在0.2‑0.3倍音速飞行速度,1千‑4千米飞行高度状态下,16°迎角范围内,升力随迎角保持线性变化,并为锥杯小翼提供较大升力,从而可为加/受油过程中抑制锥套飘摆提供有效支撑。
High-performance airfoil profile suitable for active stability augmentation of refueling taper sleeve
一种适用于加油锥套主动增稳的高性能翼型
2023-09-05
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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