Numerical simulation and test investigation on interference characteristics of grid fins with missile body at supersonic speed
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摘要:
对于呈十字型布局的栅格舵与弹身组合体来说，在有迎角存在时，位于弹身垂直平面的栅格舵会处于弹体头部分离涡的干扰区，而位于弹身水平面的栅格舵主要受弹体上洗流的影响，2种安装形式的栅格舵的气动特性会有较大差异。为研究弹身对栅格舵气动特性的干扰影响，基于典型栅格舵及栅格舵与弹身组合体布局，利用数值模拟方法对比分析了有无弹身干扰情况下栅格舵的超声速气动特性，分析了弹身对不同安装位置栅格舵的扰流特性、载荷分布，研究了由单独栅格舵气动特性转换到存在弹身干扰时栅格舵气动特性的修正方法。通过风洞验证试验，获取了2种不同安装方式栅格舵试验数据差异，验证了洗流修正方法的可行性，为建立面向工程应用的栅格舵高速风洞试验与数据修正技术提供了数据支撑。
Abstract:For cross layout grid fin-missile body configuration, the vertical grid fins will be exposed to the interference regions of head separated vortices, and thus the horizontal grid fins will be immersed in the missile body upward flow while a certain body's angle of attack exists. Therefore, there will be a greater difference in the aerodynamic characteristics of grid fins between two installation forms: vertically and horizontally. In order to investigate the missile body interference on the grid fins, numerical simulations based on typical grid fin and grid fin-missile body configuration were conducted at supersonic speed. The aerodynamic characteristics of single grid fin and grid fin with body interference were compared. Flow characteristics and load distributions of grid fins installed differently were analyzed. The correction method for the aerodynamic characteristics of grid fins with body interference obtained from the aerodynamic characteristics of single grid fin was studied. Moreover, by wind tunnel validation tests, data differences of grid fins in different installation ways were obtained, and the correction method obtained from the cross upward flow theory of the body was explored to be practicable. Thus, it provides data supports for the high-speed wind tunnel tests of grid fins and data correction technology facing engineering application.
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Key words:
- grid fin /
- upward flow /
- normal force /
- correction method /
- missile body interference
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图 2 栅格舵/弹身组合体网络拓扑结构
Figure 2. Sketch map of topogical structure of grids for grid fins/missile booly configuration
图 3 弹身干扰对栅格舵法向力系数的影响(Ma=2.0, h0/D=0.375)
Figure 3. Effect of missile body interference on normal force coefficients of grid fins (Ma=2.0, h0/D=0.375)
图 4 纵向对称剖面马赫数及流线分布(Ma=2.0, α=6°, h0/D=0.375)
Figure 4. Mach number and streamline distribution for longitudinal symmetrical profile (Ma=2.0, α=6°, h0/D=0.375)
图 5 栅格舵前缘剖面当地迎角云图(Ma=2.0, α=6°, h0/D=0.375)
Figure 5. Cloud chart of local angle of attack for leading edge profile of grid fin (Ma=2.0, α=6°, h0/D=0.375)
图 6 洗流修正结果与真实CFD计算结果对比(Ma=2.0, h0/D=0.375)
Figure 6. Comparison of upward flow correction results and real CFD results (Ma=2.0, h0/D=0.375)
图 7 栅格舵前缘剖面当地迎角云图(Ma=2.0, α=6°, h0/D=0.125)
Figure 7. Cloud chart of local angle of attack for leading edge profile of grid fin (Ma=2.0, α=6°, h0/D=0.125)
图 8 弹身干扰对栅格舵法向力系数的影响(Ma=2.0, h0/D=0.125)
Figure 8. Effect of missile body interference on normal force coefficients of grid fins (Ma=2.0, h0/D=0.125)
图 9 洗流修正结果与真实CFD计算结果对比(Ma=2.0, h0/D=0.125)
Figure 9. Comparison of upward flow correction results and real CFD results (Ma=2.0, h0/D=0.125)
图 10 弹身干扰对栅格舵轴向力系数的影响(Ma=2.0, h0/D=0.125)
Figure 10. Effect of missile body interference on axial force coefficients of grid fins (Ma=2.0, h0/D=0.125)
图 11 栅格舵前缘剖面当地马赫数云图(Ma=2.0, α=6°, h0/D=0.125)
Figure 11. Cloud chart of local Mach number for leading edge profile of grid fin (Ma=2.0, α=6°, h0/D=0.125)
图 13 弹身干扰对栅格舵法向力系数的影响
Figure 13. Effect of missile body interference on normal force coefficients of grid fins
图 14 弹身干扰对栅格舵轴向力系数的影响
Figure 14. Effect of missile body interference on axial force coefficients of grid fins
图 15 洗流修正结果与试验结果对比
Figure 15. Comparison of upward flow correction results and test results
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