摘要
提出了一种适用于整体式固体火箭冲压发动机的进气道通气减阻方案 ,并以矩形截面通气口高度、长度为变量进行了数值模拟实验 ,得到了其对阻力系数的影响规律。还给出了最佳通气方案的阻力系数随马赫数的变化规律 ,并与原始模型、进气口加堵盖方案进行了比较。最后结合一种具有常规气动布局的飞行器外形设计了模型 ,并对其进行了数值模拟研究和吹风实验 。
An inlet flow through drag reduction method is presented which can be used on solid ramjet engine.With simplified model,the height and length of the flow through configuration were numerically studied as variables to obtain their effects on inlet's drag coefficient.In addition,Comparisons were made between optimal inlet flow through model,inlet covered model and original model at several Mach numbers.Applied to a general aerodynamic configuration,this method was validated by both experimental and numerical studies.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2003年第2期185-189,216,共6页
Journal of Astronautics
