An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition
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摘要: 开展了外并联式TBCC进气道典型模态转换条件下的气动特性风洞试验研究，获得了其主要气动性能参数，并验证了所采用的CFD方法的基本可靠性。以CFD为主要手段，针对该TBCC进气道模型开展了侧板缝隙、前缘钝化以及内型面迎风台阶3方面加工偏差对进气道气动性能影响的研究。结果显示：分流板与侧板之间的缝隙导致了高、低速通道之间的窜流，在缝隙为0.5 mm时，高速通道总压恢复系数增加量可达2.13%，同时流量系数增加2.27%，这对进气道气动性能的评估产生了影响，模型侧板缝隙应小于0.5 mm；在一般加工精度（0.3 mm）下，前缘钝化半径对进气道气动性能的影响较小，进气道性能参数基本保持不变；在一般装配精度（0.5 mm）下，内型面迎风台阶对进气道流量系数基本无影响，进气道总压恢复系数的减小量小于0.44%，能够满足进气道气动性能的评估要求。Abstract: The aerodynamic performance of a typical over-under TBCC inlet mode transition model has been studied by wind tunnel experiments, and the CFD methods used have also been verified. In the present work, the influence of three typical factors on the experiment is studied by the CFD method, including the side gap, the leading edge bluntness and the forward step on the inner surface. The research results show that the gap between the splitter and the side plate leads to flow spillage between the high and low speed channels. When the gap width reaches 0.5 mm, the total pressure recovery coefficient of the high speed channel is increased by 2.13%, while the flow coefficient is improved by 2.27%. This already has an impact on the aerodynamic performance evaluation of the inlet so that the gap of the model plate should be less than 0.5 mm.The blunted radius of the leading edge has little influence on the aerodynamic performance of the inlet. For the general machining accuracy (0.3 mm), the inlet performance remains basically unchanged. For the general assembly accuracy (0.5 mm), the forward step has very little influence on the inlet flow coefficient, and the total pressure recovery coefficient of the inlet is decreased by 0.44%, which can satisfy the requirements of aerodynamic performance evaluation of the TBCC inlet.
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Key words:
- TBCC inlet /
- wind tunnel experimental model /
- side gap /
- leading edge bluntness /
- upwind step
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图 3 外并联式TBCC进气道试验模型
Figure 3. Experimental model of external parallel TBCC mode transition
图 6 进锥过程中的反压变化曲线
Figure 6. The back pressure of the high speed channel in the coning process
图 11 高速通道气动性能参数曲线
Figure 11. Aerodynamic performance parameters of the high speed channel
图 14 流场结构对比图
Figure 14. Comparison of the flow field structures obtained by experiment and CFD
图 15 沿程压力分布对比曲线
Figure 15. The static pressure distribution along the center line of TBCC inlet
图 18 TBCC进气道双通道气动参数
Figure 18. The aerodynamics performance parameters of the dual-flowpath
图 21 TBCC进气道双通道气动参数
Figure 21. The aerodynamics performance parameters of the dual-flowpath
图 26 TBCC进气道高速通道气动参数
Figure 26. The aerodynamics performance parameters of the high speed tunnel
表 1 TBCC进气道气动性能评估状态
Table 1. Conditions of TBCC inlet mode transition wind tunnel experiment
试验车次
Case实际马赫数 前室总压
/Pa分流板站位
/(°)模型状态 1 2.55 288 829.8 0 涡轮通道主要工作 2 2.55 305 258.0 4.5 两通道共同工作 3 2.55 305 692.7 9.0 冲压通道主要工作 
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表 2 有缝相对于无缝的进气道性能参数增量
Table 2. Increment of aerodynamics performance parameters for the side gap case versus basic case
通道 参数 D=0.5 mm D=1.0 mm 高速通道 ΔΦ 2.27% 6.88% Δσ 2.13% 1.09% 低速通道 ΔΦ -0.61% -1.43% Δσ 0.12% -0.081%
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表 3 前缘钝化相对于尖前缘进气道性能增量
Table 3. Increment of aerodynamics performance parameters for the blunt leading edge case versus basic case
参数 R=0.3 mm R=0.6 mm 高速通道 ΔΦ -0.10% -0.34% Δσ -0.083% -0.017% 低速通道 ΔΦ -0.83% -1.82% Δσ -0.71% -1.64%
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表 4 有台阶相对于无台阶状态的进气道性能增量
Table 4. Increment of aerodynamics performance parameters for the upwind step case versus basic case
参数 h=0.5 mm h=1.0 mm 高速通道 ΔΦ 0.044% 0.048% Δσ -0.44% -1.28%
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