Simulaton of therochemical nonequilibrium and rarefied-slip flows for hypersonic flight vehicles
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摘要:
稀薄滑移效应对高超飞行器气动特性产生重要影响。基于HyFLOW软件构建适用于热化学非平衡流动模拟的速度滑移和温度滑移边界条件，同时分别选取猎户座（Orion）飞船返回舱、OREX试验飞行器及类“哥伦比亚号”（OV102）航天飞机等典型高超飞行器，开展稀薄滑移流动模拟及其相关气动特性预测分析。研究表明：HyFLOW软件的稀薄滑移边界模型计算可靠，在预测热化学非平衡及稀薄滑移耦合效应相关的气动力、气动热特性方面具有较高的计算精度，能够满足工程复杂外形的仿真应用需求；稀薄滑移效应可显著降低热流峰值和减小热流峰值分布区域大小，相比于无滑移条件，其在类OV102航天飞机外形中预测的头部热流峰值最大降低了约45%，机翼前缘热流峰值最大降低了约20%。
Abstract:The rarefied slip effect has a significant impact on the aerodynamic characteristics of hypersonic vehicle. Based on HyFLOW software, velocity slip and temperature slip boundary conditions suitable for thermochemical nonequilibrium flows are constructed. Meanwhile, the rarefied slip flows over the usual hypersonic vehicles of the Orion reentry capsule, OREX experiment flight vehicle, and the Columbia OV102-like space shuttle are simulated, and the associated aerodynamic properties are also anticipated and studied. Research results indicate that the rarefied slip boundary model in HyFLOW software is reliable, and has high computational accuracy in predicting the aerodynamic and aerothermal characteristics related to coupling effects of thermochemical nonequilibrium and rarefied slip. It can meet the simulation application requirements of complex engineering configurations. In addition, the rarefied slip effect can significantly reduce the peak value of heat flux and its distribution area. The peak heat flow of the OV102-like space shuttle's nose is anticipated by the slip condition to be, at most, 45% less than that of the no-slip condition, and, at most, 20% less than that of the leading edge of the wing.
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Key words:
- hypersonic /
- thermochemical nonequilibrium /
- HyFLOW software /
- rarefied slip /
- space shuttle
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图 2 Orion飞船返回舱在H=85 km条件下激波位置对比
Figure 2. Comparison of shock location for Orion reentry capsule at H=85 km
图 3 H=85 km，Tw=1 184 K时，壁面滑移参数分布
Figure 3. Distribution of slip parameters on surface in H=85 km, Tw=1 184 K
图 4 H=85 km，Tw=1 184 K时，壁面热流分布对比
Figure 4. Comparison of flux components on wall surface in H=85 km, Tw=1 184 K
图 5 Orion飞船返回舱不同高度下计算驻点热流对比
Figure 5. Comparison of computed stagnation point heat flux at different altitude for Orion reentry capsule
图 7 OREX试验飞行器壁面压强对比
Figure 7. Comparison of computed pressure on surface for OREX experiment flight vehicle
图 8 OREX试验飞行器壁面热流对比
Figure 8. Comparison of computed heat flux on surface for OREX experiment flight vehicle
图 9 OREX试验飞行器不同高度下计算驻点热流对比
Figure 9. Comparison of computed stagnation point heat flux at different altitude for OREX experiment flight vehicle
图 11 类OV-102航天飞机模型的计算网格
Figure 11. Sketch of structured grid for OV-102-like space shuttle orbiter configuration
图 12 迎风面中心线热流分布
Figure 12. Heat flux profile along the center line of the windward side
图 15 H=89.95 km时，剖面曲线上热流分布对比
Figure 15. Comparisons of heat flux on profile curves at H=89.95 km
图 16 H=96.09 km时，剖面曲线上热流分布对比
Figure 16. Comparisons of heat flux on the profile curves at H=96.09 km
表 1 再入过程典型飞行条件
Table 1. Typical flight conditions of reentry process
高度[21]/km 迎角[21]/(°) 速度[21]/(m·s−1) 密度[21]/(kg·m−3) 静温[21]/K 壁温[21]/K O质量分数 O2质量分数 N2质量分数 103.14 39.86 7675.57 3.2197 ×10−7202.638 322.0 0.0313 0.1864 0.7823 96.09 39.81 7663.61 1.1431 ×10−6189.395 464.0 0.0104 0.2193 0.7703 89.95 39.78 7648.45 3.4468 ×10−6186.867 660.0 0.0018 0.2302 0.7680 85.70 41.00 7530.00 7.3160 ×10−6187.460 852.0 0 0.2330 0.7670 77.90 40.20 7420.00 2.5630 ×10−5202.740 1005.0 0 0.2330 0.7670 
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表 2 全机气动力特性参数对比
Table 2. Comparisons of total aerodynamic forces
高度/km 升力系数CL CL偏差/% 阻力系数CD CD偏差/% 俯仰力矩系数CY CY偏差/% 无滑移 滑移 无滑移 滑移 无滑移 滑移 103.14 0.7413 0.7414 0.01 1.1931 1.1907 −0.20 0.091891 0.108430 18.00 96.09 0.7942 0.7949 0.09 0.9824 0.9787 −0.38 0.089040 0.089720 0.76 89.95 0.8230 0.8230 0.00 0.8947 0.8936 −0.12 0.084506 0.084442 −0.08 85.70 0.8778 0.8771 −0.08 0.8930 0.8918 −0.13 0.088543 0.088322 −0.25 77.90 0.8670 0.8670 0.00 0.8380 0.8377 −0.04 0.078104 0.078040 −0.08
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表 3 剖面曲线上的热流峰值对比
Table 3. Comparisons of heat flux peak on the profile curves
高度/
kmQmax/（kW·m−2） 偏差/% z=0 m z=6 m z=0 m z=6 m 无滑移 滑移 无滑移 滑移 103.14 70.0333 38.5233 42.9678 34.3533 −45.00 −20.05 96.09 143.7270 136.7052 89.4312 79.1976 −4.89 −11.44 89.95 210.2339 202.8219 157.2112 146.4964 −3.53 −6.82 85.70 196.5578 192.2128 180.1191 171.5663 −2.21 −4.75 77.90 279.8960 276.4695 375.7782 366.5698 −1.22 −2.45
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