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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 paper presents the experimental results of wing freezing of a civilian aircrafts in icing wind tunnel in Italy IWT.According to the experimental states of ice wind tunnel, the ice numerical prediction based on Lagrange method and Messinger model is carried out. The ice shape and the predicted ice shape of the ice were compared and analyzed.Numerical prediction results of frost ice are in good agreement with the experimental results, and there are some differences between the ice number, the numerical results and the experimental results because: The stronger flow around changes the effect of unsteady ice accumulation on numerical prediction. (2) The icing thermodynamic model used has some limitations on simulating ice; (3) The effect of the surface roughness of the model is more sensitive.