Unsteady Flow Driven by the Counter-Flow Jets of High-Altitude Engine Based on DSMC Simulation
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摘要: 逆向发动机常用于对飞行器进行减速或分离。为研究高空稀薄条件下逆向发动机喷流和自由来流的相互作用, 构建了由两个逆向喷流和高超声速自由来流相互干扰形成的稀薄流场。通过直接模拟Monte Carlo (direct simulation Monte Carlo, DSMC)仿真发现在稀薄来流条件下会形成大面积相互干扰区, 且该干扰区存在严重非定常流动现象。初步分析认为, 该干扰区的范围和非定常演化过程与自由来流动能和逆向发动机喷流流量紧密相关。
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关键词:
- 稀薄非定常现象 /
- 逆向喷流 /
- 高空 /
- 直接模拟Monte Carlo方法 /
- 大范围干扰区
Abstract: Counter-flow engines are often used for aircraft slowing or separating. In order to study the interaction between the counter-flow jets and free stream at high altitudes, the rarefied flow driven by two counter-flow jets and hypersonic free stream was constructed. By the direct simulation Monte Carlo (DSMC) method, it is found that a large area of mutual interference will be formed under the condition of rarefied free stream, and there are serious unsteady flow phenomena in the interference area. According to preliminary analysis, the range and unsteady evolution of the interference area are closely related to the kinetic energy of free stream and the flow rate of counter-flow jets. -
图 1 DSMC采用的静态负载平衡分配方案示意图
Figure 1. Schematic diagram of static load balancing distribution scheme adopted in DSMC
图 2 姿控发动机喷流膨胀进入低密度环境的数值结果对比
Figure 2. Numerical result comparison of jet expansion into low density environments for attitude control engines
图 3 低密度风洞中辉光放电技术的实验结果
Figure 3. Experimental results in low density wind tunnel by glow discharge technology
图 4 喷流膨胀流动中沿中心线的Pitot压力比较
Figure 4. Comparison of the Pitot pressure along the central axis in the jet expansion flow
图 6 出口平面沿径向的密度和温度分布
Figure 6. Distributions of density and temperature along the radial direction of the exit plane
图 7 出口平面沿径向的法向、径向速度分布
Figure 7. Distributions of normal velocity and radial velocity along the radial direction of the exit plane
图 8 对称平面z=0内不同瞬时的压力云图
Figure 8. Pressure contours at different transient moments in the symmetry plane z=0
图 9 计算过程中飞行器前体和后体的轴向力变化趋势
Figure 9. Variation trends of axial forces of head-body and back-body of the vehicle during numerical computation
图 10 计算过程中飞行器前体和后体的法向力变化趋势
Figure 10. Variation trends of normal forces of head-body and back-body of the vehicle during numerical computation
图 11 计算过程中飞行器前体和后体的俯仰力矩变化趋势
Figure 11. Variation trends of pitching moments of head-body and back-body of the vehicle during numerical computation
图 12 不同瞬时飞行器表面的压力分布
Figure 12. Pressure distributions on the surface of the vehicle at different transient moments
表 1 出口平面的喷流气体组分及其摩尔分数
Table 1. Gas components of the jets on the exit plane and their mole fractions
gas component mole fraction/(%) CO 1.86 CO2 15.32 H2 27.59 H2O 23.95 N2 31.29 
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