비정렬 CFD 기법을 이용한 결빙 예측

다국어 초록 (Multilingual Abstract)

Ice accretion on aircraft surface can greatly deteriorate the aerodynamic performance of aircraft. Especially, air flows around a wing at glaze ice conditions are very complex and can suffer large aerodynamic penalties. Complicated horn shapes are usually found on the surfaces at glaze ice conditions by coupling effects of heat flux and shear stress. Therefore, the conventional structured CFD method has difficulty in the prediction of glaze ice shape due to its limitation on handling complex geometry. For example, negative cell volumes can be generated in the structured grids in the process of grid regeneration. In order to overcome this limitation, unstructured CFD method was employed to calculate an Eulerian-based droplet field and ice accretion on the surfaces. The developed codes were then compared with experimental data. It was shown that the collective efficiency and iced shape were in good agreement with previous results.