Drag and heat flux reduction performance of supersonic vehicle with combination model of aerospike/aerodisk and double jet
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摘要:
为降低超声速飞行器的气动力和热载荷，研究一种减阻杆/盘与双喷流组合构型，并采用数值方法分析了几何参数和喷流参数对流场特征以及减阻和防热性能的影响。结果表明：减阻杆长径比对构型的减阻效率影响较小，但对防热效率影响较大；增加减阻盘直径比，构型的减阻效率先增大后减小，防热效率先减小后增大，但当逆向喷流总压较高时，减阻盘直径比对减阻和防热效率的影响均较小；提高逆向喷流总压比，构型的减阻和防热效率一直处于较高水平，且其变化幅度均不明显；提高侧向喷流总压比，构型的减阻和防热效率均增大，减阻效率变化率增大，防热效率变化率减小；侧向喷流出口位置远离钝体头部，减阻效率增大，防热效率减小；适当选取减阻杆/盘与双喷流参数，可达到57.1%的减阻效率，同时防热效率达到100.4%。
Abstract:In order to reduce aerodynamic and thermal loads of the supersonic vehicle, a combination model of aerospike/aerodisk and double jet was studied, and the effects of geometrical parameters and jet parameters on flow field characteristics, drag and heat flux reduction were analyzed numerically. The results showed that: the length-to-diameter ratio of the aerospike had little effect on the drag reduction efficiency of the configuration, but had a great effect on the heat flux reduction efficiency. When the diameter ratio of the aerodisk increased, the drag reduction efficiency of the configuration increased first and then decreased, and the heat flux reduction efficiency decreased first and then increased. However, when the total pressure of the opposing jet was high, the diameter ratio of aerodisk had little effect on the drag and heat flux reduction efficiency. When the total pressure ratio of the opposing jet increased, the drag and heat flux reduction efficiency of the configuration was kept at a high level, and the variation range was not obvious. When the total pressure ratio of the lateral jet increased, both the drag and heat flux reduction efficiency of the configuration increased, and the change rate of the drag reduction efficiency increased, while the change rate of the heat flux reduction efficiency decreased. The location of the lateral jet was far away from the blunt body, which increased the drag reduction efficiency and decreased the heat flux reduction efficiency. The drag reduction efficiency of 57.1% and heat flux reduction efficiency of 100.4% can be achieved by properly selecting the aerospike/aerodisk and double jet parameters.
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Key words:
- supersonic flow /
- aerodisk /
- jet /
- drag reduction /
- heat flux reduction
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图 3 不同网格尺寸下沿钝体壁面压力系数分布
Figure 3. Pressure coefficient distribution along blunt body with different grids
图 4 不同网格尺寸下沿钝体壁面斯坦顿数分布
Figure 4. Stanton number distribution along blunt body with different grids
图 8 逆向喷流的密度云图和试验纹影图
Figure 8. Density contour and experimental schlieren of opposing jet
图 9 沿钝体壁面斯坦顿数分布的数值与试验结果对比
Figure 9. Comparison of Stanton number distribution along the blunt body between experiment and simulation
图 10 侧向喷流的密度云图和试验纹影图
Figure 10. Density contour and experimental schlieren of lateral jet
图 11 沿钝体壁面压力系数分布的数值与试验结果对比
Figure 11. Comparison of pressure coefficient distribution along the blunt body between experiment and simulation
图 12 基准构型和组合构型的马赫数云图及局部放大流线图
Figure 12. Mach number contours and locally magnified streamlines for the basic model and combination model
图 13 不同减阻杆长径比构型的马赫数云图和流线以及温度云图和等值线
Figure 13. Mach number contours and streamlines as well as temperature contours and isolines for different L/D
图 14 不同减阻杆长径比构型沿钝体壁面压力系数分布
Figure 14. Pressure coefficient distribution along the blunt body for different L/D
图 16 不同减阻杆长径比构型沿钝体壁面斯坦顿数分布
Figure 16. Stanton number distribution along the blunt body for different L/D
图 18 不同减阻盘直径比构型的马赫数云图和流线以及温度云图和等值线
Figure 18. Mach number contours and streamlines as well as temperature contours and isolines for different d/D
图 19 不同减阻盘直径比构型沿钝体壁面压力系数分布
Figure 19. Pressure coefficient distribution along the blunt body for different d/D
图 21 不同减阻盘直径比构型沿钝体壁面斯坦顿数分布
Figure 21. Stanton number distribution along the blunt body for different d/D
图 23 马赫数云图和流线以及温度云图和等值线（πo=0.4，πo=0.8）
Figure 23. Mach number contours and streamlines as well as temperature contours and isolines （πo=0.4，πo=0.8）
图 24 不同逆向喷流总压比构型沿钝体壁面压力系数分布
Figure 24. Pressure coefficient distribution along the blunt body for different total pressure ratios of the opposing jet
图 25 不同逆向喷流总压比构型的总阻力及其分量
Figure 25. Total drag and its components for different total pressure ratios of the opposing jet
图 26 不同逆向喷流总压比构型沿钝体壁面斯坦顿数分布
Figure 26. Stanton number distribution along the blunt body for different total pressure ratios of the opposing jet
图 27 不同逆向喷流总压比构型的防热效率
Figure 27. Heat flux reduction efficiency for different total pressure ratios of the opposing jet
图 28 马赫数云图和流线以及温度云图和等值线（πl=0.1，πl=0.6）
Figure 28. Mach number contours and streamlines as well as temperature contours and isolines （πl=0.1，πl=0.6）
图 29 不同侧向喷流总压比构型沿钝体壁面压力系数分布
Figure 29. Pressure coefficient distribution along the blunt body for different total pressure ratios of the lateral jet
图 30 不同侧向喷流总压比构型总阻力及其分量
Figure 30. Total drag and its components for different total pressure ratios of the lateral jet
图 31 不同侧向喷流总压比构型沿钝体壁面斯坦顿数分布
Figure 31. Stanton number distribution along the blunt body for different total pressure ratios of the lateral jet
图 32 不同侧向喷流总压比构型的防热效率
Figure 32. Heat flux reduction efficiency for different total pressure ratios of the lateral jet
图 33 不同侧向喷流位置构型的马赫数云图和流线
Figure 33. Mach number contours and streamlines for different locations of the lateral jet
图 34 不同侧向喷流位置构型的温度云图和等值线
Figure 34. Temperature contours and isolines for different locations of the lateral jet
图 35 不同侧向喷流位置构型沿钝体壁面的压力系数
Figure 35. Pressure coefficient distribution along the blunt body for different locations of the lateral jet
图 36 不同侧向喷流位置构型的总阻力及其分量
Figure 36. Total drag and its components for different locations of the lateral jet
图 37 不同侧向喷流位置构型沿钝体壁面斯坦顿数分布
Figure 37. Stanton number distribution along the blunt body for different locations of the lateral jet
图 38 不同侧向喷流位置构型的防热效率
Figure 38. Heat flux reduction efficiency for different locations of the lateral jet
表 2 三种网格划分细节
Table 2. Details of the three sets of grids
网格尺寸 第一层边界层高度/10−6 m 网格总数 y+ 粗网格 5.0 299591 0.91 中等网格 1.0 333454 0.18 细网格 0.5 380544 0.07 
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