摘要
升力前体由于前缘激波不能附着于前体前缘,其上下表面流场存在相互耦合,进而导致其下表面流场存在较强的横向流动,这会对腹部进气系统的设计造成不利影响。为了使前体出口流场能较好地保持二维流动特征,通过在升力前体两侧增加小角度抑流斜楔,以抑制横向流动。这种升力前体及一体化进气系统的数值模拟表明,该升力前体出口流场二维特征良好,采用该前体的进气系统能较好地维持理想的流场结构,并具有较优的性能。
Because shock wave can not attach to the leading edge of a lift forebody, the upper and lower flowfields are coupled, which induces a strong transverse flow of lower surface flow field. It may cause a negative influence on the belly-sided air inlet system. In order to make the forebody out- let flow field remain 2-D flow feature, small angle restraining wedges are put on both sides of lift forebody so as to restrain the transverse flow. Numerical simulation of the lift forebody and integra- tional inlet system shows that the 2-D feature of the lift forebody outlet flow field is perfect. The air intake system with this kind of forebody can keep the ideal flow-field structure ouite well.
出处
《火箭推进》
CAS
2014年第1期50-55,共6页
Journal of Rocket Propulsion
基金
国家863项目(2012AA702308)
关键词
升力前体
抑流楔
一体化
数值模拟
lift forebody
cross flow restraining wedge
integration
numerical simulation
