高超声速飞行器钝舵缝隙流动数值模拟研究

目前,带缝隙钝舵的缝隙引起的流场结构和气动加热规律变化,还很不明确,需要研究缝隙诱导所形成旋涡的空间分布特征和旋涡运动对物面气动加热的影响规律。通过分析高超声速钝舵缝隙气动加热问题,基于无缝隙钝舵,建立一种带缝隙钝舵简化模型。使用有限体积方法求解可压缩Navier-Stokes方程,通量采用van Leer通量向量分裂方法计算。插值采用MUSCL方法,时间项采用LU-SGS隐式方法。结果表明:无缝隙钝舵流场结构相对简单,带缝隙钝舵流场结构同无缝隙钝舵相比要更为复杂,舵轴上游缝隙内会出现马蹄形涡串结构,相应地在缝隙的上下表面均会出现马蹄形高热流区;受缝隙诱导分离再附流动的影响,在舵轴迎风面以及舵体侧面后部均形成了局部高热流区。

Numerical investigation of flow in blunt-fin gap of hypersonic vehicle

By analyzing the structure of the blunt-fin without gap, a geometrical model of the blunt-fin gap is established. The flow field structure of the blunt-fin gap is obtained by solving the compressible Navier-Stokes equations. The results show that, the flow field structure of the blunt-fin without gap is relatively simple. The numerical results are consistent with the former literature. It indicates that the computing method and the procedure of this paper is validity. Comparing with the blunt-fin without gap, the flow field structure of the blunt-fin gap is more complicated. It occur the horseshoe vortex in the gap of the upstream rudderpost, and correspondingly the gap surface form the horseshoe high heat flux. Because of the effect of vortex motion, local high heat flux region exists in the windward side of the rudderpost and the side of the rudder body.