摘要
对设计马赫数为3.5的混压式进气道,在小迎角下作了流场和边界层计算。用内激波捕捉法计算无粘流场,用积分法计算层流和湍流边界层。结果和实验数据以及特征解一致,边界层位移厚度也合理。
Numrical method of inviscid flowfield and boundary layer is developed for the hybrid compression inlet at designed Mach 3.5.The inviscid flowfields are computed by using the inter shock-capturing technique. The boundary layers of laminar and turbulent flow are all calculated through integrated method. The results presented in figures 3 to 6 demonstrate.There are all excellent agreement between results of three methods and experimental data. However, the present method can march the solution to the whole region of throat downstream of the inlet for α= 0 deg. or 3 deg. cases, whereas the shockcapturing technique in ref. 12 only to near throat. The method of characteristics can not compute three-dimensional flowfields of α = 3 deg. case. The distributions of displacement thickness is reasonable good.
出处
《空气动力学学报》
CSCD
北大核心
1990年第1期104-109,共6页
Acta Aerodynamica Sinica
关键词
超声速
进气道
流场
边界层
supersonic inlet, boundary layer, euler equation, flowfi-eld computation.
