螺旋桨旋转方向对飞机俯仰力矩特性的影响

doi:10.7527/S1000-6893.2020.23619

流体力学与飞行力学

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螺旋桨旋转方向对飞机俯仰力矩特性的影响

赵帅¹, 段卓毅², 李杰¹, 钱瑞战², 许瑞飞²

1. 西北工业大学航空学院, 西安 710072;
2. 航空工业第一飞机设计研究院, 西安 710089

收稿日期:2019-10-31 修回日期:2020-02-06 出版日期:2020-08-15 发布日期:2020-04-10
通讯作者: 李杰 E-mail:lijieruihao@nwpu.edu.cn
基金资助:
国家自然科学基金（11972304）

Effects of propeller rotation direction on pitching moment characteristics of aircraft

ZHAO Shuai¹, DUAN Zhuoyi², LI Jie¹, QIAN Ruizhan², XU Ruifei²

1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. AVIC The First Aircraft Institute, Xi'an 710089, China

Received:2019-10-31 Revised:2020-02-06 Online:2020-08-15 Published:2020-04-10
Supported by:
National Natural Science Foundation of China (11972304)

摘要/Abstract

摘要： 为了找到一种改善低平尾涡桨飞机中小迎角下纵向静稳定度的方法，采用数值模拟手段研究了螺旋桨旋转方向对飞机俯仰力矩特性的影响。基于动态面搭接网格技术和非定常雷诺平均Navier-Stokes （URANS）方程，首先对某T尾双发涡桨飞机进行了计算，验证了方法的精度和可靠性，然后对同向旋转（CO）、对转-内侧上洗（CNIU）和对转-外侧上洗（CNOU）3种低平尾涡桨飞机构型开展了数值模拟，分析了各构型的俯仰力矩变化特点及流场细节。研究结果表明：对于常见的CO构型，在小迎角下由于平尾整体效率降低，飞机的俯仰力矩曲线斜率较无动力构型大幅度下降；在小迎角下，CO构型左侧平尾的效率几乎丧失，但右侧平尾却具有良好的效率；CO构型左右两侧平尾的效率呈现巨大差异的主要原因在于两侧平尾当地的下洗梯度不同；3个构型中，CNOU构型的俯仰力矩特性最差，CNIU构型在整个中小迎角范围内都能保持良好的俯仰力矩特性。

关键词: 涡桨飞机, 低平尾, 螺旋桨旋转方向, 俯仰力矩特性, 数值模拟

Abstract: The effects of propeller rotation direction on pitching moment characteristics of aircraft are investigated through numerical simulations, aiming to discover a way to improve the longitudinal static stability of low Horizontal Tail Plane (HTP) turboprop aircraft. Based on the dynamic patched grid technique and unsteady Reynolds-averaged Navier-Stokes (URANS) equations, a T-tai twin-engine turboprop aircraft is computed first to validate the accuracy and reliability of the numerical method. Simulations are then conducted on three different low-HTP turboprop aircraft configurations respectively named co-rotating (CO), counter-rotating inboard-up (CNIU) and counter-rotating outboard-up (CNOU). The pitching moment characteristics and the flowfield details of each configuration are analyzed. Results indicate that the pitching moment curve slope of the conventional CO configuration is significantly lower than that of the unpowered configuration at low angles of attack due to the overall efficiency reduction of the HTP; The port HTP of the CO configuration almost loses its functionality at low angles of attack while the starboard HTP still maintains good efficiency; The large discrepancy in the efficiency between the port and starboard HTP of the CO configuration is mainly due to the difference in their local downwash gradients; Among the three configurations mentioned above, the CNOU configuration appears the worst in terms of pitching moment characteristics, while the CNIU configuration can maintain good pitching moment characteristics in the whole range of low and moderate angles of attack.

Key words: turboprop aircraft, low horizontal tail plane, propeller rotation direction, pithing moment characteristics, numerical simulation

中图分类号:

V211.4

赵帅, 段卓毅, 李杰, 钱瑞战, 许瑞飞. 螺旋桨旋转方向对飞机俯仰力矩特性的影响[J]. 航空学报, 2020, 41(8): 123619-123619.

ZHAO Shuai, DUAN Zhuoyi, LI Jie, QIAN Ruizhan, XU Ruifei. Effects of propeller rotation direction on pitching moment characteristics of aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(8): 123619-123619.

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E-mail：hkxb@buaa.edu.cn

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螺旋桨旋转方向对飞机俯仰力矩特性的影响

Effects of propeller rotation direction on pitching moment characteristics of aircraft

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