CAJ | 학술논문

大粒径过冷水滴超出了适航条例25部附录 C 的范围，撞击在机翼表面后可形成溢流脊状冰，危害飞行安全，但目前对于溢流结冰的气动性能影响尚未研究清楚。采用结合雷诺应力模型的数值方法，计算了 NACA 23012m 的溢流结冰翼型的最大升力系数和失速迎角，与 Lee 的实验结果符合较好，证明了该方法可用于分析溢流结冰翼型引发的流场分离。针对溢流冰脊对不同翼型影响程度差别较大的特点，对大型客机机翼超临界翼型及平尾翼型上的溢流积冰气动力进行计算，得到结论：超临界翼型在受到溢流冰脊影响时提前发生气动分离，气动性能大幅下降；平尾翼型受溢流冰脊影响较小，在大迎角下流动分离区减小。研究内容对大型客机的设计与适航审定具有一定指导意义。
대립경과랭수적초출료괄항조례25부부록 C 적범위，당격재궤익표면후가형성일류척상빙，위해비행안전，단목전대우일류결빙적기동성능영향상미연구청초。채용결합뢰낙응력모형적수치방법，계산료 NACA 23012m 적일류결빙익형적최대승력계수화실속영각，여 Lee 적실험결과부합교호，증명료해방법가용우분석일류결빙익형인발적류장분리。침대일류빙척대불동익형영향정도차별교대적특점，대대형객궤궤익초림계익형급평미익형상적일류적빙기동력진행계산，득도결론：초림계익형재수도일류빙척영향시제전발생기동분리，기동성능대폭하강；평미익형수일류빙척영향교소，재대영각하류동분리구감소。연구내용대대형객궤적설계여괄항심정구유일정지도의의。
Supercooled large droplet (SLD)is beyond the envelope described in the Appendix C of FAR 25.When the droplets impact on the surface of airfoil,they will run downstream and freeze to shape of ridge. SLD runback ice may endanger the safety of the aircraft significantly,but the aerodynamic effect of icing on vehicle performance is not completely understand.The numerical simulation of SLD icing is carried out using Reynolds Stress Model (RSM)in this paper.The computational maximum lift coefficients and stalling an-gles are agree with Lee's experimental data on NACA 23012m,the applicablitiy of RSM in analysis of flow separation resulting from runback ice is valialated.The impact degree of runback ice is quite different accord-ing to airfoil geometry,and the supercritical airfoils and tail airfoils are specially analyzed in large civil air-craft.The results demonstrate that runback ice influences the flow separation and significant deterionates aerodynamic performance of supercritical airfoils.For the tail airfoils,the aerodynamic impact of SLD icing is not so severe ,and the size of separation region is diminished at higher angles of attack.The contents of this paper have reference values in aircraft design and airworthiness certification for large civil aircraft.