论文部分内容阅读
由于具有高的升阻比,乘波构型被认为是高超声速滑翔飞行器的重点参考外形。考虑到高超声速条件下严重的气动加热问题,乘波构型的尖锐前缘需要进行钝化处理,其表面流动特征及气动性能也随之发生变化。基于参考弹道,本文分析了高超声速滑翔飞行器沿飞行轨迹的表面流场特征,并对其在典型飞行工况下的气动性能开展了数值模拟研究。结果表明:对于采用乘波布局设计的高超声速滑翔飞行器,其驻点流动存在三维效应,不能简单视为球头或圆柱绕流;钝化可以缓和严峻的受热形势,同时对其气动力性能造成影响:在2cm钝化半径条件下,其升阻比下降12.34%;高超声速滑翔飞行器的表面受热存在明显的分区特征,不同区域可采用不同的防热处理方法。
Due to its high lift-drag ratio, the configuration of the multiplication wave is considered as a key reference profile for hypersonic gliding aircraft. Considering the severe aerodynamic heating problems under hypersonic conditions, the sharp frontier of the waveride configuration needs to be passivated, and its surface flow characteristics and aerodynamic properties also change. Based on the reference trajectory, the characteristics of the surface flow field of the hypersonic gliding aircraft along the flight path are analyzed, and its aerodynamic performance under typical flight conditions is numerically simulated. The results show that for the hypersonic gliding aircraft designed by the multi-wave layout, the stagnant flow has three-dimensional effect and can not be simply regarded as the ball or cylinder flow. The passivation can mitigate the serious heating situation and cause its aerodynamic performance Effect: Under the condition of 2cm passivation radius, the lift-drag ratio is reduced by 12.34%. There is obvious zoning characteristics on the surface heat of the hypersonic gliding aircraft. Different heat-treatment methods can be used in different regions.