地面效应下前/后掠翼气动特性研究  

Investigation on Aerodynamic Characteristics of Forward/Backward Swept Wing in Ground Effect

作　　者：汪洋[1] 吴伟伟[1] 李志国[1] 

机构地区：[1]中国航天空气动力技术研究院特种飞行器总体设计部,北京100074

出　　处：《航空工程进展》2015年第4期412-418,共7页Advances in Aeronautical Science and Engineering

摘　　要：针对飞行器在地效区飞行时复杂的流场特性,通过求解定常可压N-S方程,改变机翼后掠角和地效区飞行高度,研究不同前/后掠角机翼在地效区内的气动特性。结果表明:在地效区内,随着后掠角的增大,机翼的升力系数和阻力系数呈现先增后减的变化规律,后掠角在0°附近时升力系数达到最大值,阻力系数在10°附近达到最大值;俯仰力矩系数随着后掠角增加而减小;展向流动在后掠角为0°时最小,展向流动随着后掠角增大或减小剧烈变化;机翼下洗角随着后掠角增大而减小,随着离地高度的减小而减小。研究结果可为地效飞行器的概念方案设计和优化提供理论依据。As the flow field of aircraft in ground effect is very complex,the aerodynamic characteristics of forward-swept and back swept wing in ground effect is researched carefully by solving steady compressible N-S equations and changing the back swept and flight height.The result shows that lift/drag coefficients of the wing increase first and then decrease with the increase of backswept.The lift coefficient reaches maximum when backswept is 0,while drag coefficient is the maximum at 10.Pitching moment coefficient decreases while backswept increases.The spanwise flow is the least with backswept is zero,while becoming more severe with backswept increases or decreases.Meantime,downwash angle decreases with back-swept angle increasing,while decreases with flight height decreasing.The result can provide the theoretical basis for the programming and optimization of aircraft in ground effect.

关 键 词：地面效应 后掠角 气动特性 下洗角 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]