NACA0012翼型等离子体冰形调控试验

doi:10.7527/S1000-6893.2021.26283

流体力学与飞行力学

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NACA0012翼型等离子体冰形调控试验

刘雪城, 梁华, 宗豪华, 谢理科, 苏志

空军工程大学等离子体动力学国家级重点实验室，西安 710038

收稿日期:2021-08-26 修回日期:2021-09-30 出版日期:2022-09-15 发布日期:2021-11-10
通讯作者: 梁华,E-mail:lianghua82702@126.com E-mail:lianghua82702@126.com
基金资助:
国家自然科学基金(12002384)；国家重点实验室基金(614220210200112)

Experiment on plasma ice shape modulation based on NACA0012 airfoil

LIU Xuecheng, LIANG Hua, ZONG Haohua, XIE Like, SU Zhi

Laboratory of Science and Technology on Plasma Dynamics, Air Force Engineering University, Xi 'an 710038, China

Received:2021-08-26 Revised:2021-09-30 Online:2022-09-15 Published:2021-11-10
Supported by:
National Natural Science Foundation of China (12002384); National Key Laboratory Foundation of China (614220210200112)

摘要/Abstract

摘要： 冰形调控是指采用等离子体激励将有限功率集中使用，将危险的展向连续冰调控成更为安全的间断冰，改善飞机容冰飞行能力，在保证飞行器气动性能及飞行安全的前提下，拓宽飞机容冰飞行安全边界的技术。为验证等离子体冰形调控的可行性，在冰风洞中开展等离子体防除冰试验，结果表明纳秒脉冲等离子体冰形调控激励器能够将翼型前缘连续冰调控为间断冰，形成类波浪形前缘，初步验证了等离子体冰形调控的能力。为探究冰形调控技术对翼型气动性能的改善效果，在30 m/s的来流速度下，在NACA0012翼型上间断布置3D打印典型冰形(明冰、霜冰、混合冰)，并在风洞中测试其气动性能，对比分析不同的有冰与无冰区域比例、冰条宽度L对翼型气动性能的影响。结果表明：明冰冰形下，有冰∶无冰=1∶1(L=2 cm)时气动性能改善效果最佳，与全冰状态相比最大升力系数提高34.8%，迎角10°时阻力系数降低86.0%。霜冰和混合冰冰形下，分别在有冰∶无冰=3∶2(L=6 cm)、有冰∶无冰=3∶2(L=4 cm)的调控方案下气动性能改善效果最好，最大升力系数分别提高了19.7%、30.6%，阻力系数明显降低。

关键词: 等离子体, 防除冰, 冰形调控, 升力, 阻力

Abstract: Ice shape modulation is a technology that significantly reduces the power of anti-icing and broadens the safety boundary of ice-tolerant flight under the premise of ensuring the aerodynamic performance and flight safety of the aircraft. It uses the power excited by the plasma actuator to change the dangerous spanwise continuous ice into safer intermittent ice, thereby improving the ice-containing flight capability of the aircraft. To verify the feasibility of the technology, plasma anti-icing experiments were carried out in the ice wind tunnel. The results show that the nanosecond pulse plasma actuator can change the continuous ice in the airfoil front edge into discontinuous ice. The formation of a wave-like front edge preliminarily verifies the ability of plasma ice shape modulation. To explore the effect of the technology on the aerodynamic performance of the wing, 3D printed typical ice shapes (glaze ice, rime ice, and mixed ice) were intermittently arranged on the NACA0012 airfoil at an incoming flow velocity of 30 m/s. The aerodynamic performance was tested in the wind tunnel, and the influence of different ratios of icing area to non-icing area and the width of the icicle L on the aerodynamic performance of the airfoil was compared and analyzed. The results show that for the glaze ice, the aerodynamic performance has the best improvement when the ratio of icing area to non-icing area is equal to 1∶1 (L=2 cm), with the maximum lift coefficient being increased by 34.8% and the drag coefficient at the angle of attack of 10° being reduced by 86.0% in comparison with the full-ice state. For the rime ice and mixed ice, the aerodynamic performance has the best improvement when the ratio is equal to 3∶2 (L=6 cm) and to 3∶2 (L=4 cm), with the maximum lift coefficient being increased by 19.7% and 30.6% respectively and the drag coefficient being significantly reduced in comparison with the full-ice state.

Key words: plasma, anti-/de-icing, ice shape modulation, lift, drag

中图分类号:

V211

刘雪城, 梁华, 宗豪华, 谢理科, 苏志. NACA0012翼型等离子体冰形调控试验[J]. 航空学报, 2022, 43(9): 126283-126283.

LIU Xuecheng, LIANG Hua, ZONG Haohua, XIE Like, SU Zhi. Experiment on plasma ice shape modulation based on NACA0012 airfoil[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 126283-126283.

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NACA0012翼型等离子体冰形调控试验

Experiment on plasma ice shape modulation based on NACA0012 airfoil

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