Investigation on performance enhancement of flap based on dual synthetic jets
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摘要: 飞机在起降和大机动过程中，襟翼偏角过大会导致襟翼上方出现流动分离，从而使舵面效率降低甚至失效。为有效解决舵效问题，提出了一种基于合成双射流的襟翼舵效增强技术，针对无缝襟翼，探究了合成双射流不同控制参数对升力、舵效的影响规律。研究结果表明：合成双射流能在襟翼表面形成周期性涡结构，增强边界层底部低速流体与主流的动量交换，提高边界层抗逆压梯度的能力；襟翼处合成双射流可有效提高升力、增强舵效；当合成双射流无量纲驱动频率为3.89、动量系数为3.01 × 10–3时，舵效增强效果最好。此外，还设计、制作了合成双射流激励器与机翼一体化模型，并开展了飞行试验，可实现的滚转角速度达15.69 (°)/s，验证了合成双射流增强舵效的可行性和有效性。Abstract: When the aircraft is in the process of taking off, landing and flexible maneuvering, flow separation occurs above the flap and rudder which is caused by the large deflection angle. It reduces the performance of the flap and rudder, or even makes them ineffective. In order to solve this problem, a performance enhancement technology of flap based on array dual synthetic jets was proposed. Aiming at seamless flap, the influence of different dual synthetic jets driving parameters on the lift force and flap performance was investigated. The investigation results show that the dual synthetic jets can generate periodic vortex structures above the flap surface, which enhanced the momentum exchange between the low-velocity air in the boundary layer and the main flow. These vortex structures can also strengthen the ability of the boundary layer to resist the adverse pressure gradient. The array dual synthetic jets at the flap can effectively increase the lift force and enhance the flap performance. The flap performance enhancement is more effective when the dimensionless driving frequency is 3.89 and the momentum coefficient is 3.01 × 10–3. The integrated model of the array dual synthetic jets actuator combined with the wing was designed and fabricated, and the flight test was carried out. The rolling angular velocity could achieve 15.69 (°)/s, which verifies the feasibility and effectiveness of performance enhancement of flap based on dual synthetic jets.
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Key words:
- dual synthetic jet /
- performance enhancement of flap /
- numerical simulation /
- flight test
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图 3 升力系数、阻力系数的数值模拟与试验结果对比
Figure 3. Comparison between numerical simulation and test results of lift coefficient and drag coefficient
图 4 不同驱动频率控制气动系数对比
Figure 4. Comparison of aerodynamic coefficients of different driving frequencies
图 5 不同动量系数控制$C_\mu $气动系数对比
Figure 5. Comparison of aerodynamic coefficients of different momentum coefficient
图 6 不同控制参数的速度云图（α = 4°）
Figure 6. Velocity diagram of different control parameters (α = 4°)
图 7 不同频率下的速度云图及压力系数分布（α = 6°）
Figure 7. Velocity nephogram and pressure coefficient distribution at different frequencies (α = 6°)
图 8 不同动量系数下的速度云图及压力系数分布（α = 4°）
Figure 8. Velocity nephogram and pressure coefficient distribution at different momentum coefficient (α = 4°)
图 10 无人机示意图和DSJA安装位置示意图
Figure 10. Size of flight platform and DSJA installation position
图 14 施加右侧DSJA控制后的飞行参数变化
Figure 14. Flight parameters after applying right DSJA control
表 1 不同网格下的升、阻力系数
Table 1. Lift and drag coefficients with different number of grids
网格数 CL CD 60000 1.4589 0.1449 80000 1.5115 0.1517 150000 1.5119 0.1527 
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