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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.
The forming characteristics of ridges and the effect of ice ridges on the aerodynamic characteristics of the ridges are analyzed.A multi-step icing procedure is developed based on the classic Messinger icing model, The results of the calculation and the experimental results agree well with each other, which shows the correctness of the heat and mass coupling algorithm.On the basis of this, the ice ridges under different ambient temperature, flight speed and different heating power And the aerodynamic characteristics of the wing were calculated and analyzed.The results show that ice ridges form and develop mainly outside the thermal protection limit and close to the thermal protection limit under non-frost conditions, Under the conditions, ice ridges are mainly formed on the lower surface of the wing, but significant icing occurs in the thermal protection zone. The icing under this condition has a great destructive effect on the aerodynamic characteristics of the wing.