脉冲射流对环量控制翼型气动性能的影响

雷玉昌; 张登成; 张艳华; 苏光旭

doi:10.13700/j.bh.1001-5965.2020.0560

脉冲射流对环量控制翼型气动性能的影响

doi: 10.13700/j.bh.1001-5965.2020.0560

1.
空军工程大学研究生院，西安 710051
2.
空军工程大学航空工程学院，西安 710038

详细信息

通讯作者:
张登成, E-mail: dengcheng_zhang@163.com

中图分类号: V211.3; V224⁺.5
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- 被引次数: 0
出版历程
- 收稿日期: 2020-09-28
- 录用日期: 2020-12-11
- 网络出版日期: 2022-03-20

Effect of pulsed jet on aerodynamic performance of circulation control airfoil

1.
Graduatee School, Air Force Engineering University, Xi'an 710051, China
2.
Aeronautics Engineering College, Air Force Engineering University, Xi'an 710038, China

More Information

Corresponding author: ZHANG Dengcheng, E-mail: dengcheng_zhang@163.com

摘要

摘要:
定常射流在大迎角下气动性能较差，借助脉冲射流能够有效改善大迎角下的气动性能，并减少射流所需质量流量。采用非定常数值模拟的方法进行了脉冲射流作用下的环量控制翼型气动特性计算和流场分析。总结了占空比和频率分别对时均升力和升力脉动幅值的影响趋势；分析了不同迎角下的脉冲射流流动机理；进一步指出了射流动量系数的影响规律，并借助脉冲射流和定常射流的叠加效应有效缓解了升力脉动现象。结果表明：低占空比、同等升力系数下，脉冲射流可大幅度减小质量流量，但升力脉动幅值较大；小迎角下随频率增大，升力系数先增大后减小，但整体变化幅度不大，大迎角下随频率增大，升力系数持续性增大；脉冲射流能够推迟失速迎角，扩宽环量控制技术的可用迎角，并且随动量系数增大，这种优势更加明显；借助脉冲射流与定常射流的叠加效应，能够有效缓解脉冲射流作用下的升力脉动现象，达到飞行使用条件。
- 脉冲射流 /
- 环量控制 /
- 数值模拟 /
- 升力脉动 /
- 增升 /
- 失速
Abstract:
The aerodynamic performance of steady jet is poor at high angle of attack. With the help of pulsed jet, the aerodynamic performance at high angle of attack can be effectively improved and the mass flow rate of jet can be reduced. The unsteady numerical simulation method is used to calculate the aerodynamic characteristics and analyze the flow field of the circulation control airfoil under pulsed jet. The effects of duty cycle and frequency on the amplitude of time-averaged lift and lift pulsation are summarized. The flow mechanism of pulsed jet at different angles of attack is analyzed. Furthermore, the influence law of jet momentum coefficient is pointed out, and the lift pulsation phenomenon is effectively alleviated with the help of the superposition effect of pulsed jet and steady jet. The results show that, under low duty cycle, the pulsed jet can greatly reduce the mass flow rate under the same lift coefficient, but the amplitude of lift pulsation is larger at the same time. At low angle of attack, the lift coefficient increases at first and then decreases with the increase of frequency, but the overall change is not obvious, and at high angle of attack, the lift coefficient increases continuously with the increase of frequency. The pulsed jet can delay the stall angle of attack and widen the angle of attack, and this advantage becomes more obvious with the increase of momentum coefficient. With the help of the superposition effect of the pulsed jet and the steady jet, the lift pulsation under the pulsed jet can be effectively alleviated and the flight conditions can be achieved.
- pulsed jet /
- circulation control /
- numerical simulation /
- lift pulsation /
- lift enhancement /
- stall

HTML全文

图 1 翼型相关参数示意图

Figure 1. Sechematic map of airfoil shape parameters

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图 2 翼型计算网格划分

Figure 2. Airfoil's computational grid generation

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图 3 不同时间步长下的时均升阻力系数

Figure 3. Time-averaged lift and drag coefficient at different time step sizes

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图 4 升力系数仿真与实验对比

Figure 4. Comparison of lift coefficient between simulation and experiment

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图 5 35 Hz脉冲射流下时均压力系数分布

Figure 5. Time-averaged pressure coefficient distribution under 35 Hz pulsed jet

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图 6 不同质量流量下的时均升力系数对比

Figure 6. Comparison of lift coefficient at different mass flow rates

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图 7 35 Hz脉冲射流下时均升力系数时域曲线对比

Figure 7. Comparison of lift coefficient time-domain curves at 35 Hz pulsed jet

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图 8 不同频率下的升力系数增量和脉动幅值对比

Figure 8. Comparison of lift coefficient and pulsation amplitude at different frequencies

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图 9 翼型涡量图和流线图

Figure 9. Airfoil vorticity and streamlines

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图 10 200 Hz脉冲射流下时均升力系数时域曲线对比

Figure 10. Comparison of lift coefficient time-domain curves at 200 Hz pulsed jet

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图 11 升力系数对比

Figure 11. Comparison of lift coefficient

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图 12 气动品质因子对比曲线

Figure 12. Aerodynamic quality factor comparison

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图 13 不同r_sp下的时均升力系数与脉动幅值对比曲线

Figure 13. Comparison of lift coefficient and pulsation amplitude at different r_sp

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图 14 翼型后缘流线图

Figure 14. Airfoil trailing edge streamlines

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表 1 不同占空比对应的射流速度

Table 1. Jet velocity corresponding to different duty cycle

DC/%	V_jet.max/(m·s^-1)	V_jet.min/(m·s^-1)
30	173.5	0
50	134.4	0
70	113.6	0
90	100	0

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