旋翼风洞试验洞壁干扰参数影响及敏感性分析  

Analysis of impact and sensitivity of wall interference parameters in wind tunnel test of rotors

作　　者：刘向楠 邵天双[1,2] 刘少腾 LIU Xiangnan;SHAO Tianshuang;LIU Shaoteng(AVIC Aerodynamics Research Institute,Harbin 150001,China;Key Laboratory of Aviation Technology for Aerodynamics for Low Speed and High Reynolds Number,Harbin 150001,China)

机构地区：[1]中国航空工业空气动力研究院,哈尔滨150001 [2]低速高雷诺数气动力航空科技重点实验室,哈尔滨150001

出　　处：《空气动力学学报》2025年第3期78-86,I0002,共10页Acta Aerodynamica Sinica

摘　　要：在旋翼风洞试验中,模型旋翼产生的下洗流在风洞洞壁的约束下会产生强烈的洞壁干扰。引起洞壁干扰的参数众多,为了探究各试验参数对洞壁干扰的影响,首先建立基于Heyson方法的洞壁干扰分析方法,并在中国航空工业空气动力研究院FL-10风洞的开、闭口试验段开展了验证试验,验证了方法的有效性;然后基于该方法分析了各试验参数对洞壁干扰的影响;最后基于Sobol算法计算了洞壁干扰量对各试验参数的灵敏度,揭示了其敏感程度。结果表明:桨毂中心越靠近风洞中心,洞壁干扰相对越小;开、闭口试验段的旋翼洞壁干扰影响相反,且开口段的洞壁干扰影响大于闭口段;前进比、拉力系数、旋翼模型尺寸为洞壁干扰的主要影响参数,其中前进比起主要作用,其总灵敏度达0.894,拉力系数和旋翼模型尺寸的总灵敏度系数分别为0.144和0.155,为次要影响参数。研究结果为揭示旋翼洞壁干扰影响机理提供了参考。During rotor wind tunnel tests,the downwash flow generated by the model rotor produces significant wall interference due to the constraints imposed by the wind tunnel walls,with multiple parameters contributing to this interference.To investigate the impact of test parameters on the tunnel wall interference,an analysis method based on the Heyson approach was first established.Verification tests were conducted in both open and closed test sections of the FL-10 wind tunnel at the AVIC Aerodynamics Research Institute,confirming the effectiveness of the method.Subsequently,this method was utilized to analyze the parameter effects on tunnel wall interference.Finally,the Sobol algorithm was employed to calculate the sensitivity of wall interference to various test parameters.The results indicate that wall interference is minimized when the hub center is aligned with the wind tunnel center.The effects of wall interference on the rotor performance are opposite in open and closed wind tunnels,with more pronounced interference observed in the open tunnel.Among the investigated parameters,the advance ratio emerges as the most significant factor,exhibiting a sensitivity coefficient of 0.894.The thrust coefficient and the rotor model scale represent secondary influencing parameters,with total sensitivity coefficients of 0.144 and 0.155,respectively.These findings provide valuable insights into the mechanism of rotor-wall interference effects.

关 键 词：旋翼 风洞试验 洞壁干扰 灵敏度 FL-10风洞 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]