Shock-shock interactions of high mach leading edge
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摘要:
采用数值模拟方法及激波极曲线方法开展高马赫数平板-后掠前缘流动结构与热环境特性研究。结果表明：随着后掠角增加，平板斜激波与后掠前缘激波相交，依次形成Ⅳ、Ⅴ、Ⅵ类激波-激波干扰。整体上随着后掠角增加，激波-激波干扰引起的局部压力、热流增量逐渐减小，但过渡型Ⅳ类激波-激波干扰诱导干扰区热流、压力可能低于典型Ⅴ类激波-激波干扰。激波-激波干扰诱导热流随攻角增加而增加，随雷诺数增加而降低。同时，建立了基于临界折转角的高马赫数前缘激波-激波干扰类型判别准则，判别结果经过数值模拟结果验证。形成了高马赫数前缘激波-激波干扰关系、干扰位置及干扰类型图谱，能为高马赫数飞行器总体方案和气动外形设计与优化提供有力支撑。
Abstract:Validated numerical approach and shock polar diagrams method were employed to investigate the flow structure and aerodynamic heating environment around high-mach flat- sweepback leading edge. The results demonstrated that with the increase of sweepback, the flat angle shock and leading edge shock crossed, and then Ⅳ, Ⅴ, Ⅵ shock-shock interactions were formed in turn. In general, the local pressure and heat flux increment caused by shock-shock interaction decreased with the increase of leading edge, but heat flux and pressure of interference zone under the transition Ⅳ shock-shock interaction might be lower than that under the typical Ⅴ shock-shock interaction. Moreover, it was found that the induced heat flux increased with the increase of attack angle, and decreased with the increase of Reynolds number. Also, a convenient discriminant method for high-Mach leading edge shock-shock interaction was provided based on critical deflection angle analysis. The discriminant results were validated against numerical results. The shock-shock interaction relation, interaction location and interference type graph for high-Mach leading edge was presented. The findings could benefit not only high-Mach aircraft integrated design, but also aerodynamic configuration optimization.
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图 3 圆柱前缘中心线热流结果对比
Figure 3. Heat flux comparison along the center line of leading ledge for column
图 10 前缘中心线热流压力（案例1）
Figure 10. Heat flux and pressure at leading edge center line （case 1）
图 11 前缘中心线热流压力（案例2）
Figure 11. Heat flux and pressure at leading edge center line （case 2）
图 13 数值纹影及热流对比（λ=0°）
Figure 13. Comparison of numerical schlieren and heat flux （λ=0°）
图 18 Ⅳ类干扰临界转折角激波极曲线图
Figure 18. Shock polar diagrams for critical turning angle of type Ⅳ
图 19 Ⅵ类干扰临界转折角激波极曲线图
Figure 19. Shock polar diagrams for critical turning angle of type Ⅵ
表 1 第一层网格高度对热流的影响对比
Table 1. Heat flux comparison of different first layer mesh height
网格编号 第一层网格高度/m 无量纲峰值热流 1 5×10−6 4.23 2 1×10−6 4.75 3 5×10−7 4.80 
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表 2 网格总量影响对比
Table 2. Comparison of different total mesh number
网格编号 网格总量 无量纲峰值热流 4 220×450×120（总1.2×107） 4.08 2 250×500×120（总1.5×107） 4.75 6 300×580×150（总2.6×107） 4.74
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表 3 来流状态
Table 3. Incoming flow state
案例 来流
马赫数来流雷诺数/
m−1来流静压/
Pa来流静温/
K来流攻角/
（°）1 8 1.6×105 79.78 270.65 10 2 8 1.6×105 79.78 270.65 20 3 8 2.0×106 79.78 270.65 10 4 6 1.2×105 79.78 270.65 5
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表 4 实验来流状态
Table 4. State of test air
参数 数值 来流马赫数 5.96 来流雷诺数/m−1 6.89×106 来流攻角/（°） 0 来流温度/K 412.28
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表 5 案例1典型区域流动参数
Table 5. Flow parameter at typical region of case 1
干扰类型 λ/（°） β3/（°） θ3/（°） β2/（°） θ2/（°） Ⅳ 15 85 >43.8 75 >42.2 Ⅴ 30 70 >43.8 60 40.9 Ⅵ 45 55 40.1 45 32.8 Ⅵ 60 40 30.6 30 21.2 Ⅵ 75 25 18.6 15 6.7
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表 6 典型区域流动参数
Table 6. Flow parameter at typical region
案例 λ/（°） β3/（°） θ3/（°） β2/（°） θ2/（°） 干扰类型 2 30 80 >43.8 60 37.4 Ⅴ 4 30 65 42.3 60 35.5 Ⅵ
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