高超声速稀薄流曲形槽道ABLE翼型气动特性分析

Aerodynamic Analysis of a Curved-Channel ABLE Airfoil in Hypersonic Rarefied Flow

将曲形槽道人工钝头(Artificial Blunted Leading Edge,ABLE)概念应用于对称菱形翼中,针对飞行器可能出现的高空稀薄流流域进行分析,旨在探究ABLE概念在近空间稀薄流流域内的适用情况。利用直接模拟蒙特卡罗(DSMC)方法,对比分析了攻角为0~10°下菱形翼与ABLE菱形翼的气动性能,并探讨了槽道构型参数对翼型气动性能的影响。结果表明,槽道参数设计合理时,ABLE概念能以较小的热流增量为代价显著提升翼型的升阻比,增升效果明显;与连续流情况下有明显差异,在稀薄流中,虽然槽道将前缘驻点高压区移除,但是由于槽道增加的湿润面积致使粘性阻力大幅度增加,导致ABLE概念翼型减阻性能不佳;除此之外,由于明显的稀薄气体效应,翼型气动力性能严重劣化。

An airfoil,equipped with a curved-channel artificial blunted leading edge(ABLE),is a good alternative to increase the lift-to-drag ratio.For this purpose,a curved-channel ABLE was applied to a diamond airfoil to analyze the aerodynamic performance in high-altitude hypersonic rarefied flow.The drag reduction and lift increment efficiency of the ABLE airfoil were analyzed in the hypersonic rarefied flow at angle of attack of 0~10°.The variation in the aerodynamic performance of the ABLE airfoil with partial channel configurations was determined using the direct simulation Monte Carlo(DSMC)method.The results showed that with suitable ABLE configuration and parameter values,the concept of ABLE can help reduce the drag coefficient,improve the lift coefficient,and obtain a better lift-to-drag ratio without considerable aerothermal tradeoff.However,the drag reduction effect of the curved-channel airfoil in the rarefied flow is much lower than that in the continuous flow,because the increased wetted area will increase the viscous drag obviously.The overall aerodynamic performance is significantly deteriorated because of the rarefaction effect of the atmosphere.