基于实验设计方法的高超声速飞机前缘型线优化分析

发布时间：2018-07-08 13:56

本文选题：高超声速飞机 + 吸气式飞行器　；参考：《力学学报》2016年02期

【摘要】：为探索前缘线变化对吸气式高超声速飞机气动性能的影响,基于一种旁侧进气布局翼身融合体构型,在飞行马赫数6,攻角4?和高度26 km的巡航飞行条件下,结合运用增量修正参数化设计方法、均匀实验设计方法和计算流体力学模拟,分析了飞行器前缘型线与其升阻力系数及纵向压心等性能参数间的关系.计算结果表明,前缘线形状对飞行器升阻力系数明显高于其对纵向压心影响,设计空间范围内升力系数变化约21.3%,阻力系数变化约31.8%,升阻比变化范围约10.63%,但相对压心变化范围仅为3.87%.在此基础上,通过对典型构型物面压力分布进行分析,发现前缘线形状适当弯曲可利用飞行器下表面侧壁压缩产生的高压气流,利用二者的耦合效应使飞行器获得额外的升力增量.
[Abstract]:In order to explore the effect of the change of leading edge line on the aerodynamic performance of hypersonic aspirated aircraft, based on a flanking intake configuration, the flight Mach number 6, attack angle 4? Combined with incremental modified parametric design method, uniform experimental design method and computational fluid dynamics simulation. The relationship between the leading edge profile of the aircraft and the performance parameters such as lift resistance coefficient and longitudinal pressure center is analyzed. The calculated results show that the influence of the shape of the leading edge line on the lift resistance coefficient of the aircraft is obviously higher than that on the longitudinal center of the vehicle. In the design space, the lift coefficient changes about 21.3g, the resistance coefficient about 31.8and the rise-to-drag ratio about 10.63, but the relative pressure center is only 3.87. On the basis of this, by analyzing the pressure distribution of the typical configuration, it is found that the high pressure airflow produced by the compression of the side wall of the lower surface of the aircraft can be used in the proper bending of the leading edge line. Using the coupling effect, the aircraft can obtain additional lift increment.
【作者单位】：中国科学院力学研究所高温气体动力学国家重点实验室;中国空气动力研究与发展中心;中国航天科工集团31研究所;
【基金】：国家自然科学基金资助项目(11372324,11572333)
【分类号】：V221.3

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