| 摘要: |
| 侧板构型和唇口位置是影响侧压式进气道性能的关键参数。选取了5个具有一定代表性的状态点对前/后掠进气道模型进行了计算和分析,重点比较了当侧板前/后掠时进气道的流量系数、压升、出口气流均匀度等性能。通过对比分析,发现侧板前掠时进气道的流量系数、压升大于侧板后掠结果,且进气道出口流场更均匀。当马赫数较低时,前/后掠进气道性能差别比较明显:同为50%溢流窗,来流马赫数4时,侧板前掠的进气道流量系数比侧板后掠的情形高出7.7%;而当来流马赫数为8.09时,侧板前掠的进气道流量系数仅高2.6%。 |
| 关键词: 高超声速进气道 侧压+ 前/后掠+ 数值仿真 |
| DOI： |
| 分类号:V211.48 |
| 基金项目:国家“八六三”计划资助项目(2005AA723042) |
|
| Calculation and comparison of forward/backward swept sidewall compression scramjet inlets |
|
LI Hua1, JIA Di2, FAN Xiao-qiang3, LI Xiao-yu4
|
|
1.Inst.of Aerospace and Material Engineering,National Univ.of Defence Technology,Changsha 410077,China;2.Inst.of Aerospace and Material Engineering,National Univ.of Defence Technology,Changsha 410078,China;3.Inst.of Aerospace and Material Engineering,National Univ.of Defence Technology,Changsha 410079,China;4.Inst.of Aerospace and Material Engineering,National Univ.of Defence Technology,Changsha 410080,China
|
| Abstract: |
| Configurations of sidewall and location of cowl have significant influence on the performance of sidewall-compression scramjet inlets.A series of numerical simulation are completed with the variation of flight height,Mach number and cowl position for forward and backward swept sidewall compression inlets.Compared with backward swept sidewall compression inlets,inlets with forward leading edges display better performances,demonstrated by higher mass capture ratio and static pressure raise,as well as more uniform out-let flow field.The results indicate that the differences are more obvious at low flight Mach number when the cowl is backward located.Mass capture ratio of forward-swept inlet is 7.7% higher than that of backward-swept inlet at Ma 4;however,the difference decrease to 2.6% when the inflow Mach number increases to Ma 8. |
| Key words: Hypersonic inlet Sidewall compression Forward/backward Numerical simulation |
