Investigation of runback ice during aircraft anti-icing process
-
摘要: 对机翼防冰过程中冰脊的形成特点及冰脊对机翼气动特性的影响进行了计算分析.基于经典的Messinger结冰模型开发了多步结冰程序,对不同条件下过冷水滴的撞击结冰进行了热质耦合计算,计算结果和文献试验结果吻合较好,表明该热质耦合算法的正确性.在此基础上对不同环境温度、飞行速度和不同加热功率等条件下冰脊的生长特点和机翼的气动特性进行了计算分析.结果表明:在非霜冰条件下,冰脊主要在热防护极限外并紧挨着热防护极限的位置处形成和发展,而在霜冰条件下,冰脊主要在机翼下表面形成,但是在热防护区域内有显著的结冰出现,该条件下的结冰对机翼的气动特性具有较大的破坏性.Abstract: The calculation was performed on runback ice and its effects on the aerodynamic characteristics of the airfoil. A multi-step ice accretion code was developed based on the classical Messinger icing model and it was used to predict the ice shapes in different conditions. Good agreement between the calculation results and the experimental data indicates the heat-mass coupled arithmetic is correct. Base on the arithmetic, the growth of the runback ice and the aerodynamic characteristics of the airfoil were calculated. The results indicate that the runback ice is likely to form outside the thermal protection area and begins to grow near the position of the thermal protection limit in non-rime ice conditions. However, in rime ice conditions, the runback ice is more likely to form at the lower surface of the airfoil and there is significant ice accretion in the thermal protection area and because of this the aerodynamic characteristics of the airfoil is destroyed greatly.
-
Key words:
- anti-icing /
- runback ice /
- heat-mass coupled /
- icing model /
- aerodynamic characteristics
-
[1] Pereira C M.Status of NTSB aircraft icing certification-related safety recommendations issued as a result of the 1994 ATR-72 accident at Roselawn,IN [R].AIAA 1997-0410,1997 [2] Bond T H,Miller D R,Potapczuk M G.Overview of SLD engineering tools development.AIAA 2003-386,2003 [3] Bragg M B.Aircraft aerodynamic effects due to large droplet Ice Accretions [R].AIAA 96-0932,1996 [4] 李延.表面粗糙度与飞机结冰的相关性研究 [D].北京:北京航空航天大学航空科学与工程学院,2011
Li Yan.Study on relativity between icing surface roughness and aircraft icing [D].Beijing:School of Aeronautic Science and Engineering,Beijing University of Aeronautics and Astronautics,2011(in Chinese)[5] Alegre N.Full-scale runback ice:accretion and aerodynamic study [D].Cranfield University,2010 [6] 蒋胜矩,李凤蔚.基于N-S方程的翼型结冰数值模拟[J].西北工业大学学报,2004,22(5):559-560
Jiang Shengju,Li Fengwei.A better numerical simulation of ice accretion on airfoil[J].Journal of Northwestern Polytechnical University,2004,22(5):559-560 (in Chinese)[7] Shin J,Berkowitz B,Chen H,et al.Prediction of ice shapes and their effect on airfoil performance [R].AIAA 91-0264,1991 [8] von Donehoff A,Horton E.A low-speed experimental investigation of the effect of a sandpaper type of roughness on boundary-layer transition [R].NACA Report No.1349,1956 [9] Beaugendre H,Morency F,Habashi W G.Roughness implementation in fensap-ice:model calibration and influence on ice shapes[J].Journal of Aircraft,2003,40(6):1212-1215 [10] Gent R W,Dart N P,Cansdale J T.Aircraft icing[J].Philosophical Transactions:Mathematical,Physical and Engineering Sciences,2000,358(1776):2873-2911 [11] Shin J,Bond T H.Results of an icing test on a NACA 0012 airfoil in the NASA Lewis icing research tunnel [R].AIAA-92-0647,1992 -
点击查看大图
计量
- 文章访问数: 1563
- HTML全文浏览量: 54
- PDF下载量: 709
- 被引次数: 0
下载:
