民用飞机机翼结冰试验与数值预测  

Test and numerical prediction of ice accretions on civil aircraft wing

作　　者：张强[1] 陈迎春 周涛[1] 白峰[1] ZHANG Qiang CHEN BAI Ying-chun ZHOU Tao Feng(Shanghai Aircraft Design and Research Institute, Commercial Aircraft Corporation of China Limited, Shanghai 201210, China Science and Technology Committee, Commercial Aircraft Corporation of China Limited, Shanghai 200120, China)

机构地区：[1]中国商用飞机有限责任公司上海飞机设计研究院,上海201210 [2]中国商用飞机有限责任公司科技委,上海200120

出　　处：《航空动力学报》2017年第1期22-26,共5页Journal of Aerospace Power

摘　　要：描述了某民用飞机在意大利IWT(icing wind tunnel)冰风洞的机翼结冰试验结果.根据冰风洞试验状态点,开展了基于拉格朗日方法和Messinger模型的冰形数值预测,并对试验冰形和数值预测冰形进行了对比分析.霜冰的数值预测结果与试验结果一致性良好,对于明冰,数值结果和试验结果存在一定的差异,原因在于:1明冰结冰过程中较强的绕流变化增大了冰积聚非定常效应对数值预测的影响;2采用的结冰热力学模型对明冰的模拟存在一定局限性;3明冰对于冰风洞设备工况和试验模型表面粗糙度的影响更为敏感.The ice accretion test results on civil aircraft wing in Italy IWT（icing wind tunnel）were described.The numerical prediction of ice shapes was conducted based on the Lagrange method and Messinger model according to the icing wind tunnel test states.The icing shape test and numerical prediction results were compared and analyzed.A conclusion can be drawn that the numerical results and test data of the rime ice are consistent,while there is difference between those of the glaze ice.The possible reasons can be listed as follows：（1）the airflow variation during the glaze ice accretion strengthens the unsteady effect on icing prediction;（2）the icing thermal model adopted has some limitation for glaze ice prediction;（3）the icing wind tunnel work states and the test model roughness are sensitive to glaze ice accretion.

关 键 词：民用飞机 结冰 冰风洞 试验 数值预测 

分 类 号：V244.1[航空宇航科学与技术—飞行器设计]