高超声速验证飞行器助推分离段流场数值研究

Numerical study of flow past hypersonic research vehicle with detaching booster

为了模拟有相对运动的多体非定常绕流 ,发展了基于弹簧近似的非结构动网格方法及耦合动网格的Euler解算器。作为方法验证 ,模拟了俯仰振动的NACA0 0 12翼型绕流 ,计算结果与实验及文献结果非常接近。采用二维近似外形 ,对高超声速验证飞行器助推分离段流场进行了数值研究 ,得到了不同时刻由于多体相对运动形成的干扰流场结构以及分离过程的气动力参数。

Dynamic unstructured grid methodology and ALE Euler solver for complex multi body flows involving moving boundaries were developed Pitching NACA0012 airfoil flow was simulated as a demonstration of the method, results of which compare well with that of experiment and literature The methodology then was applied to simulate the flow past Hyper X research vehicle when separating with its booster Though the simulation performed on 2 D approximate configuration, complex flow structures at different instants were obtained as well as force and moment coefficients during the whole course