Dynamic boundary layer transition wind tunnel test of blunt cone
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摘要: 钝锥飞行器俯仰振动时，非对称边界层转捩区前后移动相对于俯仰角运动的滞后将产生显著的非定常气动效应，导致飞行器俯仰动稳定性降低，严重时甚至会导致运动失稳。将基于气浮轴承的动态试验技术与转捩红外测量技术相结合，建立了钝锥动态转捩风洞试验技术。该技术采用气浮轴承提供俯仰运动自由且阻尼极低的支撑环境，采用红外热像仪实时测量飞行器表面整体转捩状态。开展了9°钝锥标模动态转捩试验，研究模型绕俯仰轴转动时边界层转捩区前后移动的非定常气动作用与飞行器运动的耦合效应。测量试验观察到了动态转捩试验迎角振荡现象，并发现了转捩区前后移动相对于迎角振荡的滞后现象，获得了转捩滞后时间。Abstract: The time delay effects of the boundary layer transition movement on the surface compared to aircraft pitching oscillation should produce serious unstable aerodynamic moments, which probably decrease the aerodynamic stabilities in the pitch direction, even leading to unpredicted pitching divergence in the reentry flight of the blunt cone. A boundary layer dynamic transition test technology of the blunt cone in the hypersonic wind tunnel is improved, using a gas bearing as support of the test model in order to realize free rotation of the test model in the longitudinal direction with extremely low damping moment. In addition, an infrared thermo-graphic system is used to observe and estimate the boundary layer transition distribution on the model, to study the dynamic coupling phenomenon and interaction between boundary layer transition and longitudinal rotation of the model. A series of tests are completed using the blunt cone model of which the half cone angle is 9 degree, to study dynamic coupling effects between boundary layer transition and longitudinal rotation. As a conclusion, an unsteady oscillation phenomenon of angle of attack was observed when dynamic boundary layer transition occurred, and at the same time, the delay phenomenon and delay time of boundary layer transition to angle of attack rotation were identified.
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Key words:
- blunt cone /
- dynamic /
- boundary layer transition /
- wind tunnel test /
- coupling
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图 6 钝锥标模转捩试验模型表面温度图（1#试验）
Figure 6. Temperature graphic of boundary layer transition wind tunnel test （1# test）
图 8 模型表面温度图及其Canny边缘线图（1#试验）
Figure 8. Temperature graphics and correlated transition-lines solved with Canny edge detector method （1# test）
图 9 转捩运动相对于迎角运动的滞后时间
Figure 9. Time delay of transition area movement compared to angle of attack oscillation
图 10 转捩运动相对于迎角运动的相位差
Figure 10. Phase difference of area movement compared to angle of attack oscillation
表 1 试验参数表
Table 1. Inflow parameters of wind tunnel tests
试验序号 总压/MPa 总温/K 单位雷诺数 1# 2.96 506.3 2.43×107 2# 2.70 487.0 2.34×107 3# 1.77 460.0 1.70×107 
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表 2 转捩滞后时间分析结果
Table 2. Delay time of transition area movement compared to angle of attack oscillation
迎角下行过程 迎角上行过程 迎角峰值时刻/s 转捩后退时刻/s Δt1/s 相位差/（°） 迎角谷值时刻/s 转捩前进时刻/s Δt2/s 相位差/（°） 14.39 14.41 0.02 47.4 14.31 14.37 0.06 142.1 14.54 14.57 0.03 71.1 14.46 14.50 0.04 94.7 14.69 14.73 0.04 94.7 14.61 14.65 0.04 94.7 14.83 14.86 0.03 71.1 14.76 14.80 0.04 94.7 14.98 15.01 0.03 71.1 14.91 14.94 0.03 71.1 15.14 15.17 0.03 71.1 15.06 15.10 0.04 94.7
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