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基于粘性干扰效应的理论研究基础,利用数值模手段获得复杂高超声速外形的气动力数据,建立了完全气体条件下纵向气动力系数的粘性干扰模型;以相对正交距离的形式,给出了粘性干扰模型预测结果的不确定度量化分析。研究表明:从粘性干扰参数的理论研究出发,结合数值模拟手段,是研究高超声速复杂外形粘性干扰效应的有效手段;利用粘性干扰参数和迎角的组合,可以建立具有一定精度的粘性干扰模型,从而将不同高度、马赫数和迎角下的高超声速气动力数据进行关联;利用具有较高计算效率的Euler方程结果,结合粘性干扰模型的修正,获得大规模的用于飞行器设计的气动数据,并建立相应的气动数据库,对于工程设计是一种较为高效、经济的选择。
Based on the theoretic foundation of viscous interference effect, the aerodynamic data of complex hypersonic profile are obtained by means of numerical mode, and the viscous interference model of longitudinal aerodynamic coefficient under complete gas condition is established. In the form of relative orthogonal distance, the viscosity Uncertainty Analysis of Prediction Results of Interference Models. The research shows that viscous interference parameters can be used to study viscous interference effect of hypersonic hypersonic system based on theoretical research of viscous interference parameter and numerical simulation method. Viscous interference model with certain accuracy can be established by the combination of viscous interference parameters and angle of attack, So the hypersonic aerodynamic data of different heights, Mach numbers and angles of attack are correlated. Based on the Euler equation with higher computational efficiency and the modification of the viscous interference model, the aerodynamic data for aircraft design are obtained, And establish the corresponding pneumatic database, which is a more efficient and economical choice for engineering design.