基于总体布局参数的飞机静稳定性研究

基于飞机初步设计阶段所得到的总体布局参数,建立飞机气动导数数值模型,对亚声速静稳定性进行估算。最后对所建立的数值模型进行算例分析,并与计算流体动力学(CFD)方法所求的气动导数、实际飞行试验数据进行对比,结果表明,基于总体布局参数计算的气动导数方法快速、合理。

Static Stability Analysis Based on Conceptual Design

To estimate the static stability of aircraft in subsonic regime,a numerical calculation model of aerodynamic derivatives is developed based on aircraft geometry parameters from the conceptual design phase.An example for aerodynamic derivatives is given.A comparison of the numerical calculation results to predicted aerodynamic derivatives by a computational fluid dynamics(CFD) method and test data shows that the numerical calculation method based on an aerodynamic configuration generated in the conceptual design phase is rapid and reasonable in operation.