Research on improvement measures of transverse heading of general aircraft based on spoiler
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摘要: 为了适应强侧风条件下的短距起降，大型通用飞机要求在大侧滑角时依然有较好的横航向稳定性。以某大型通用运输机为对象，开展横航向特性研究工作，发现该飞机的横航向试验数据存在拐折现象，并利用理论分析和风洞试验开展了基于扰流板的通用飞机横航向稳定性的改善措施研究。研究表明：数据出现拐折现象的根本原因是机翼发生了局部分离——带侧滑角后机身引起的强烈上洗大幅度增加了迎风侧中央翼当地迎角，导致该迎角超过模型翼型失速迎角、发生局部分离。在机身侧面加装扰流板的方式干扰了上洗气流的流动，从而抑制了机翼上表面气流的提前分离，消除了横航向特征曲线的拐折现象，改善了飞机的横航向稳定性。Abstract: In order to adapt to the short take-off and landing requirement under the condition of strong side wind, the large general-purpose aircraft should still have good transverse heading stability at large side slip angle. In this paper, the transverse heading characteristics of a large general-purpose transport aircraft were studied, it is found that there is a turning phenomenon in the transverse heading heading test date of the aircraft. And the measures to improve the transverse heading stability of the general aircraft based on spoiler were studied by means of the wind tunnel test and theoretical analysis. The results show that the root cause of the turning phenomenon of the data is the local separation of the wing, that as the strong upwash caused by the fuselage with side slip angle greatly increases the local angle of the attack of the center wing on the windward side, local separation occurs when the local angle of attack of the center wing on the windward side exceeds the stall angle of attack of the model airfoil. The installation of a spoiler on the side of the fuselage interferes with the flow of the upwash air, and as a result the advance separation of the airflow on the upper surface of the wing is restrained, the turning phenomenon of the transverse heading characteristic curve is eliminated, and the lateral heading stability of the aircraft is improved.
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Key words:
- yaw and lateral stability /
- spoiler /
- wind tunnel test
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表 1 采用的措施对应表
Table 1. Corresponding table of measures
具体措施 措施1 起落架舱前伸修形 措施2 翼根修型 措施3 在翼根处阻挡、抑制上洗气流 措施4 翼身修型 措施5 机翼下方机身侧面加扰流板 
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