大型民机巡航构型前缘缝翼气动载荷设计  

Aerodynamic load design of slats in the cruise configuration of large civil aircraft

作　　者：谭林林[1] 符梁栋 TAN Linlin;FU Liangdong(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《飞行力学》2022年第4期76-80,共5页Flight Dynamics

摘　　要：针对大型民用客机研制与适航取证中的巡航构型前缘缝翼气动载荷计算问题,根据某型民用客机飞行试验增升装置试飞实测的压力分布,并对比分析了风洞试验压力分布,采用CFD进行定性分析后,提出了更为准确合理的巡航构型缝翼气动载荷设计方法。在原有的外表面压力分布基础上,内表面压力不再赋零处理,补充内表面压力分布作为载荷计算的输入,并考虑密封性系数的影响,由此得到的缝翼载荷与试飞实测基本一致,验证了缝翼载荷设计方法的合理性和可靠性。所提方法已在工程中得到验证和应用。Aiming at the aerodynamic load calculation of slats in cruise configuration during the development and airworthiness certification of large civil aircraft, a more accurate and reasonable aerodynamic load design method for slat of cruise configuration was proposed, according to the pressure distribution of flight and wind tunnel tests, and the qualitative analysis of CFD. On the basis of the original outer surface pressure distribution, the pressure distribution in the slat cabin was included, which was not set to zero. In addition, the influence of the sealing coefficient was considered. The obtained slat loads were basically consistent with the flight test results, which verified the reliability and rationality of the slat load design method. At present, this method has been verified and applied in actual design work.

关 键 词：大型民用飞机 前缘缝翼 气动载荷 密封性 

分 类 号：V215.1[航空宇航科学与技术—航空宇航推进理论与工程]