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摘要:
为了探究进口拐角波系对超燃冲压发动机喷管的壁面压力分布作用机制，考虑进口拐角波系对超燃冲压发动机尾喷管性能的影响，开展不同拐角波及其强度对喷管气动参数影响的数值模拟分析。进行数值方法有效性和网格无关性验证，利用不同的前后台阶来形成进口拐角波系，研究了不同波系和波系强度对喷管气动性能的影响。结果表明，进口拐角波系造成的进口非均匀对喷管气动性能造成显著影响，其中推力系数在上下壁面存在后台阶时最大增加13.98%，升力在下壁面前台阶时提高94.32%，而俯仰力矩则在上壁面前台阶、下壁面后台阶时最多降低35.47%。当喷管进口存在单侧前台阶时，随台阶高度增加，升力与俯仰力矩的变化趋势一致；而喷管进口存在单侧后台阶时，结论相反。此外，壁面台阶对喷管性能的影响是相互独立的，且基本符合线性叠加原理。
Abstract:In order to explore the mechanism of the effect of inlet corner wave system on the wall pressure distribution of scramjet nozzle and investigate the influence of the inlet corner wave system on the performance of a scramjet nozzle, the numerical simulation and analysis of the influence of different corner waves and their intensity on the aerodynamic parameters of the nozzle were carried out. The effectiveness of the numerical method and the grid independence were verified. Different forward/backward steps were used to form the inlet corner wave system, and the influence of different wave systems and wave system intensities on the aerodynamic performance of the nozzle was studied. The results show that the inlet non-uniformity caused by the inlet corner wave system has a significant impact on the aerodynamic performance of the nozzle, in which the thrust coefficient can be increased by 13.98% at most when there is a backward step on the upper and lower walls, and the lift can be increased by 94.32% when there is a forward step on the lower wall. However, the pitching moment can be reduced by 35.47% at most when there is a forward step on the upper wall and a backward step on the lower wall. When there is a single-sided forward step at the nozzle inlet, the changing trend of lift and pitching moment is consistent with the increase in step height; when there is a single-sided backward step at the nozzle inlet, the conclusion is different. In addition, the influence of wall steps on nozzle performance is independent of each other and basically conforms to the linear superposition principle.
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Key words:
- scramjet /
- nozzle /
- expansion wave/shock wave /
- forward/backward steps /
- aerodynamic performance
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图 8 不同网格尺度获得的下壁面压力分布
Figure 8. Pressure distributions on lower walls obtained from different grid scales
图 9 不同网格尺度获得的下壁面摩擦系数分布
Figure 9. Friction coefficient distribution on lower walls obtained from different grid scales
图 11 典型前后台阶下的流场结构示意
Figure 11. Flow field structure under typical forward and backward step
图 12 上壁面在前台阶作用下和下壁面在后台阶作用下的流场结构示意
Figure 12. Flow field structure with forward and backward step on upper/lower wall
图 13 $ u_{+3\%} $台阶下喷管流场压力和马赫数分布云图
Figure 13. Cloud charts of pressure and Mach number distributions in nozzle flow field under step of $ u_{+3\%} $
图 14 $ u_{-3\%} $台阶下喷管流场压力和马赫数分布云图
Figure 14. Cloud charts of pressure and Mach number distributions in nozzle flow field under step of $ u_{-3\%} $
图 15 上壁面拐角波系下的喷管气动性能变化曲线
Figure 15. Variation curves of aerodynamic performance of nozzle under corner wave system of upper wall
图 16 $ u_{+3\%} $,$ u_{-3\%} $和${u_0}$作用下的壁面沿程压力分布
Figure 16. Pressure distributions along walls under$ u_{+3\%} $,$ u_{-3\%} $, and $ u_{0} $
图 17 $ d_{+3\%} $台阶下喷管流场压力和马赫数分布云图
Figure 17. Cloud charts of pressure and Mach number distributions in nozzle flow field under step of $ d_{+3\%}$
图 18 $ d_{-3\%} $台阶下喷管流场压力和马赫数分布云图
Figure 18. Cloud charts of pressure and Mach number distributions in nozzle flow field under step of $ d_{-3\%}$
图 19 下壁面拐角波系下的喷管气动性能变化曲线
Figure 19. Variation curves of aerodynamic performance of nozzle under corner wave system of lower wall
图 20 $ d_{+3\%}$,$ d_{-3\%}$、$ d_{0}$作用下的壁面沿程压力分布
Figure 20. Pressure distributions along walls under $ d_{+3\%}$,$ d_{-3\%}$, and $ d_{0}$
图 21 ${u_ - }{d_ + }$台阶下喷管流场压力和马赫数分布云图
Figure 21. Cloud charts of pressure and Mach number distributions in nozzle flow field under step of ${u_ - }{d_ + }$
图 22 双侧${u_ - }{d_ + }$与单独${u_ - }$和${d_ + }$作用下的升力变化曲线
Figure 22. Comparison of nozzle lift variation under step of $ u_-d_+ $ and corresponding single-sided step type
图 23 $ {u_+}{d_+} $,$ u_-d_-$,$ u_{+}d_-$,$ u_-d_+ $下的喷管性能变化曲线
Figure 23. Variation curves of aerodynamic performance of nozzle under $ {u_+}{d_+} $,$ u_-d_-$,$ u_{+}d_-$, and $ u_-d_+ $
表 1 计算域进出口流动参数
Table 1. Flow conditions of inlet and outlet in calculation domain
参数 数值 计算域进口马赫数Main 1.76 计算域进口静压Pin/Pa 45454.52 计算域进口静温Tin/K 1 821.97 环境压力Pe/Pa 3 466.0 环境温度Te/K 219.57 巡航马赫数Ma0 5.00 巡航高度H/km 23.00 
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