Experimental study on influence of incoming total temperature on hypersonic boundary layer transition
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摘要: 壁温比/温度是高超声速边界层转捩研究中需要引起重视的重要参数。在中国空气动力研究与发展中心Φ2 m激波风洞（FD−14A）的头部钝度0.05 mm、半锥角7°尖锥模型上开展试验，流场马赫数分别为9.86、9.97，单位雷诺数分别为8.9 × 106/m、8.4 × 106/m，总温分别为1332.2 K、956.6 K。在马赫数、雷诺数、噪声水平、壁温大致相同条件下，研究风洞总温对高超声速边界层转捩的影响，采用点热流传感器测量转捩位置和高频脉动压力传感器测量边界层脉动特性，分别采用γ−Reθ−MT修正模型的转捩预测结果和线性稳定性理论结果与试验结果进行对比。结果表明采用γ−Reθ−MT修正转捩模型计算的尖锥模型热流分布结果与风洞试验结果吻合良好，转捩位置基本一致，表明该模型具有较高的可信度；PCB传感器测量的压力脉动和线性稳定性理论分析结果相互印证，展示了风洞条件下高低总温两个流场第2模态波频谱特性。Abstract: Wall-temperature-ratio/temperature is a parameter that needs attention in the study of hypersonic boundary layer transition. The boundary layer transition experiment was carried out in CARDC Φ2 m shock tunnel, the model is a 7° half-angle cone model with the nosetip bluntness of 0.05mm, the Mach number is 9.86 and 9.97, the unit Reynolds number is 8.9 × 106/m and 8.4 × 106/m, and the total temperature is 1332.2 K and 956.6 K, respectively. Under the conditions of approximately the same Mach number, Reynolds number, noise level and wall temperature, the effect of the total temperature of the wind tunnel on the transition of the hypersonic boundary layer is studied. The heat flux sensor is used to measure the transition position and the high frequency fluctuation pressure sensor is used to measure the fluctuation characteristics of the boundary layer. The experimental results are compared with the transition prediction results of the γ−Reθ−MT model and the linear stability theory results, respectively. The heat flux distribution results of the cone calculated by the transition model are in good agreement with the wind tunnel test results, and the transition positions obtained experimentally and theoretically are basically the same, indicating that the numerical calculation method of the transition model has high reliability. The pressure fluctuation results measured by the PCB sensor and the theoretical analysis results of the linear stability are mutually confirmed, showing the second mode wave spectrum characteristics of the two cases of high and low total temperature under wind tunnel conditions.
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图 3 低总温流场脉动压力功率谱
Figure 3. PSD of pressure fluctuations of flow-field at low total temperature
图 4 高总温流场脉动压力功率谱
Figure 4. PSD of pressure fluctuations of flow-field at high total temperature
图 5 高低总温流场中性曲线对比
Figure 5. Comparison of neutral curves of flow fields at high and low total temperatures
图 8 高低总温流场的2#PCB压力脉动功率谱与线性稳定性分析N值对比
Figure 8. comparison of PSD of 2# PCB and N factor from LST computation for high and low total temperature flow fields
图 9 高低总温流场3#PCB压力脉动功率谱与线性稳定性分析N值对比
Figure 9. comparison of PSD of 3# PCB and N factor from LST computation for high and low total temperature flow fields
图 10 高低总温流场4#PCB压力脉动功率谱与线性稳定性分析N值对比
Figure 10. comparison of PSD of 4# PCB and N factor from LST computation for high and low total temperature flow fields
图 11 高低总温流场5#PCB压力脉动功率谱与线性稳定性分析N值对比
Figure 11. comparison of PSD of 5# PCB and N factor from LST computation for high and low total temperature flow fields
图 12 高低总温流场6#PCB压力脉动功率谱与线性稳定性分析N值对比
Figure 12. comparison of PSD of 6# PCB and N factor from LST computation for high and low total temperature flow fields
表 1 风洞来流参数
Table 1. Wind tunnel incoming flow parameters
高总温 低总温 总压P0（MPa） 22.54 12.05 总温T0（K） 1332.2 956.6 马赫数Ma 9.86 9.97 单位雷诺数Re∞/L（1/m） 8.90 × 106 8.40 × 106 密度ρ∞（kg/m3） 0.026 0.0199 静温T∞（K） 69.4 47.3 静压P∞（Pa） 529.8 279 速度u∞（m/s） 1674 1397 
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表 2 PCB传感器坐标及当地边界层流态
Table 2. PCB sensor coordinates and local boundary layer flow regimes
PCB 1# 2# 3# 4# 5# 6# 7# 8# X（mm） 125 205 285 365 445 525 605 685 流态 L L R R R T T T
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