Volume 39, Number 3, June 2021
|Page(s)||566 - 575|
|Published online||09 August 2021|
An active control method for reducing sonic boom of supersonic aircraft
School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China
叶正寅(1963-), 西北工业大学教授、博士生导师, 主要从事高超声速飞行器气动弹性及飞行器气动布局设计。e-mail: firstname.lastname@example.org
Sonic boom reduction has been an urgent need to develop the future supersonic transport, because of the heavy damages of the noise pollution. This paper provides an active control method for the supersonic aircraft to reduce the sonic boom, wherein a suction slot near the leading edge and an injection slot near the trailing edge on the airfoil suction surface are opened, and the mass flow sucked in near the leading edge is equal to the mass flow injected near the trailing edge. The diamond and 566 airfoils are adopted as the baseline airfoil to verify the capability of the active control method, and the effects of the suction and injection location, the mass flow rate and the attack angle on the ground boom signature, the maximum overpressure, the drag coefficients and the ratio of lift to drag are studied in detail. The results show that the proposed active control method can significantly reduce the sonic boom, and the reduction of the sonic boom intensity is more sensitive to the injection near the trailing edge than the suction near the leading edge. Applying this active control method to the diamond (NACA0008) airfoil, when the mass flow rate is 6.5 kg/s(7.5 kg/s), the value of maximum positive overpressure is decreased by 12.87%(12.85%), the value of maximum negative overpressure is decreased by 33.83%(56.77%) and the drag coefficient is decreased by 9.50%(10.96%). It can be seen that the method proposed in this paper has great benefits in the reduction of sonic boom and provides a useful reference for designing a new generation of lower sonic boom supersonic aircraft.
声爆抑制问题是新一代环保型超声速客机研发过程中亟需解决的关键技术瓶颈之一。提出了一种降低超声速飞行器声爆的主动控制方法，主要是在翼型下表面前缘附近处开口进行吸气，同时在翼型下表面后缘附近进行喷气，且保持吸气量与喷气量相等。分别以菱形翼型和NACA0008翼型作为基准算例，研究了吸气口与喷气口位置、气体质量流量以及飞行迎角对地面声爆最大过压、阻力系数以及升阻比的影响。结果表明该方法能够显著地降低超声速飞行器声爆水平以及阻力，并且后缘处喷气比前缘处吸气更容易达到降噪的效果。将主动控制方法应用于基准菱形（NACA0008）翼型后，当气流质量流量为6.5 kg/s（7.5 kg/s）时，最大正过压值降低了12.87%（12.85%），最大负过压值的绝对值降低了33.83%（56.77%），阻力系数降低了9.50%（10.96%）。可见文中提出的低声爆方法效果良好，为新一代低声爆超声速客机的设计提供了有益的参考。
Key words: supersonic aircraft / sonic boom / shock wave / suction injection / noise reduction
关键字 : 超声速客机 / 声爆 / 激波 / 吸喷气 / 降噪
© 2021 Journal of Northwestern Polytechnical University. All rights reserved.
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