| 摘要: |
| 从三维薄层近似N S方程出发 ,采用高效ENO差分格式 ,对位于弹体中部两侧的双喷管发动机喷流与马赫数Ma∞ =0 7～ 0 9、攻角α =0°～ 10°飞行条件下弹体绕流形成的干扰流场进行了数值模拟。研究发现与无喷流情况相比较 ,引入喷流使升力和俯仰力矩增加 ,压心后移 ;在飞行攻角一定时 ,马赫数对飞行器气动力特性影响较小 ;有侧风干扰时 ,喷流增强了航向稳定性。对零攻角情况喷管安装和喷管出口不对称带来侧向力和偏航力矩也进行了研究。计算结果与飞行实验观测现象定性一致 |
| 关键词: 导弹推进 气动特性 双喷管发动机 射流 数值仿真 |
| DOI： |
| 分类号:V430 |
| 基金项目: |
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| Effect of double-nozzle engine jet flow on vehicle aerodynamic characteristics |
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LIU Jun, LIU Wei
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Inst.of Aerospace and Material Engineering, National Univ.of Defence Technology, Changsha 410073,China
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| Abstract: |
| Interaction between vehicle and double nozzle engine on condition of Mach number Ma ∞ =0 7～0 9 and attack angle α =0°～10°was studied numerically using new type ENO scheme. The models with double nozzle engine jets were compared with that has no jet, it was found that the lift and pitching moment of vehicle increased with jets and the influence of Mach number on aerodynamics characteristics was little than attack angle. The influence of the asymmetry used by jets on the aerodynamics of vehicle was studied. The lateral stability induced by wind was improved with double nozzle engine jets. |
| Key words: Missile propulsion Aerodynamic characteristic Double nozzle engine Jet flow Numerical simulation |
