Numerical simulation on drag and heat reduction of hypersonic spike-aerodisk-self-coupled stamping lateral jet concept
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摘要:
对高超声速杆-盘-自耦合冲压横向射流构型的减阻防热效果进行数值模拟。相比单纯减阻杆-气动盘，杆-盘-自耦合冲压横向射流构型将剪切层推离壁面，扩大了靠近钝体的回流区，并将分离激波推离减阻杆，再附激波强度明显减弱，组合构型减阻防热特性显著提高。研究了杆-盘-自耦合冲压横向射流构型的减阻防热机理，并研究了不同参数对减阻防热效果的影响：在研究范围内，侧向排气口角度从30°增加到90°，减阻防热效果不断提升，但是当侧向排气角度从90°增加到120°，减阻防热效果略有降低。对于侧向多排气口，第二侧向排气口距离钝体壁面越远，减阻防热性能越好。在研究范围内，减阻防热效果最好的构型，与同参数减阻杆-气动盘构型相比，钝体壁面斯坦顿数峰值降低39.7%，构型阻力系数降低19.3%。
Abstract:The drag and heat reduction effect of hypersonic spike-aerodisk-self-coupled stamping lateral jet configuration was numerically simulated. Compared with the simple spike-aerodisk, the spike-aerodisk-self-coupled stamping lateral jet configuration pushed the shear layer away from the wall, enlarged the recirculation zone near the blunt body, and pushed the separating shock away from the spike. The strength of the attachment shock was significantly weakened, and the drag and heat reduction characteristics of the combined configuration were significantly improved. The drag and heat reduction mechanism of the spike-aerodisk-self-coupled stamping lateral jet configuration was studied, and the influences of different parameters on the drag and heat reduction effect were discussed. Within the study range, the drag and heat reduction effect was continuously improved when the lateral jet angle increased from 30° to 90°, but when the lateral jet angle increased from 90° to 120°, the drag and heat reduction effect decreased slightly. For lateral multiple jets, the farther the second lateral jet was from the blunt body wall surface, the better the drag and heat reduction performance. The configuration with the best drag and heat reduction effect was compared with the configuration with the same parameter spike-aerodisk, finding that the peak value of Stanton number on blunt body wall was reduced by 39.7%, and the drag coefficient of configuration was reduced by 19.3%.
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图 3 不同网格钝体壁面压力系数分布
Figure 3. Pressure coefficient distributions along blunt body surface for different grids
图 4 不同网格钝体壁面斯坦顿数分布
Figure 4. Stanton number distributions along blunt body surface for different grids
图 5 实验纹影图像与计算云图对比
Figure 5. Comparison of experimental schlieren image and computational contour
图 6 计算与实验钝体壁面热流密度对比
Figure 6. Comparison of heat flux along blunt body surface between computational and experimental results
图 12 不同构型沿钝体壁面压力系数对比
Figure 12. Comparison of pressure coefficient along blunt body surface for different configurations
图 13 不同构型沿钝体壁面斯坦顿数对比
Figure 13. Comparison of Stanton number along blunt body surface for different configurations
图 14 不同构型阻力系数对比
Figure 14. Comparison of drag coefficients for different configurations
图 18 不同侧向排气孔角度槽道内质量流量对比
Figure 18. Comparison of mass flow rate in channel for different jet angles
图 19 不同侧向排气孔角度下钝体壁面压力系数对比
Figure 19. Comparison of pressure coefficient along blunt body surface for different jet angles
图 20 不同侧向排气孔角度下钝体壁面斯坦顿数对比
Figure 20. Comparison of Stanton number along blunt body surface for different jet angles
图 21 不同侧向排气孔角度的阻力系数对比
Figure 21. Comparison of drag coefficients of different jet angles
图 23 单孔/双孔构型流场马赫数云图对比
Figure 23. Comparison of Mach number contours for single jet/double jets
图 24 单孔/双孔构型钝体壁面压力系数对比
Figure 24. Comparison of pressure coefficient along blunt body surface with single jet/double jets
图 25 单孔/双孔构型钝体壁面斯坦顿数对比
Figure 25. Comparison of Stanton number along blunt body surface with single jet/double jets
图 26 单孔/双孔构型阻力系数对比
Figure 26. Comparison of drag coefficients of single jet/double jets
表 1 网格信息
Table 1. Grid information
类型 网格数量 壁面第一层网格高度/10−5 m 粗网格 220525 3.5 中等网格 316262 1 密网格 355274 0.5 
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表 2 双侧向排气孔构型计算工况
Table 2. Cases for working conditions for double jets
计算工况 Lr1 Lr2 Case-1 0.5 0.3 Case-2 0.5 0.4 Case-3 0.6 0.5 Case-4 0.7 0.5
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