高超声速乘波体扩容设计及流场快速预测

为发展一种兼具乘波体高升阻比和升力体高容积率的气动设计与预测方法,开展了3个方面的研究工作。基于升力体和乘波体融合设计理念,提出了一种大容积率、高升阻比的乘波前体的扩容设计方法。对扩容设计的乘波前体进行了数值模拟,获得了典型设计参数对前体容积率、升阻比等气动性能参数的影响规律。基于本征正交分解理论和径向基函数建立了高超声速乘波前体流场结构和气动性能参数的快速预测模型,并对扩容设计的乘波前体流场开展了快速预测研究。研究表明:相比于未扩容之前,高度为5、10 mm时,容积增加8.00%和15.00%;基于本征正交分解理论的快速预测方法可精确、快速地获得不同几何设计参数下乘波前体的流场,预测误差不高于2.00%。 

Design of improving volumetric efficiency of hypersonic waverider and rapid prediction of flow field

In order to develop an aerodynamic design and prediction method that combines the high lift-to-drag ratio of waverider and the high volumetric efficiency of lifting vehicle, research was carried out in three aspects. Based on fusion design concept of lifting vehicle and waverider, a hypersonic waverider design method with large volumetric efficiency and high lift-drag ratio was proposed. Numerical simulation was carried out to obtain the influence of typical design parameters on the aerodynamic performance, such as the volumetric efficiency and lift-drag ratio. Based on the proper orthogonal decomposition method and radial basis function, a rapid prediction model of hypersonic waverider flow field and aerodynamic performance was established and the rapid prediction of flow field was studied. The research showed that compared with ordinary waverider, when the height was 5 and 10 mm, the volume increased by 8.00% and 15.00%; the rapid prediction method based on the proper orthogonal decomposition method can accurately and quickly obtain the flow field of waverider with different design parameters and the prediction error was not higher than 2.00%.