本文選題：民用飛機　切入點：結冰　出處：《航空動力學報》2017年01期

【摘要】：描述了某民用飛機在意大利IWT(icing wind tunnel)冰風洞的機翼結冰試驗結果.根據冰風洞試驗狀態(tài)點,開展了基于拉格朗日方法和Messinger模型的冰形數值預測,并對試驗冰形和數值預測冰形進行了對比分析.霜冰的數值預測結果與試驗結果一致性良好,對于明冰,數值結果和試驗結果存在一定的差異,原因在于:1明冰結冰過程中較強的繞流變化增大了冰積聚非定常效應對數值預測的影響;2采用的結冰熱力學模型對明冰的模擬存在一定局限性;3明冰對于冰風洞設備工況和試驗模型表面粗糙度的影響更為敏感.
[Abstract]:The results of wing icing test of a civil aircraft in an ice tunnel of IWT(icing wind tunneling in Italy are described.According to the state point of ice wind tunnel test, the ice shape numerical prediction based on Lagrangian method and Messinger model is carried out, and the ice shape is compared and analyzed.The numerical prediction results of frost ice are in good agreement with the experimental results, and there are some differences between the numerical results and the test results for the open ice.The reason is that the strong change of flow around the ice during the freezing process increases the influence of the unsteady effect of ice accumulation on the numerical prediction. The thermodynamic model of ice formation has some limitations on the simulation of open ice.The influence of the operating conditions of the equipment and the surface roughness of the test model is more sensitive.
【作者單位】： 中國商用飛機有限責任公司上海飛機設計研究院;中國商用飛機有限責任公司科技委;
【分類號】：V211.74;V244.15

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