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随着对生产成本、性能和可靠性、环境要求的不断提高,未来运输类飞机的发展趋势是具有更大的载重、更短的起降距离、更低的污染排放和噪声,因此迫切需要采用更高效和简单的增升和控制技术,而采用狭缝吹气的主动流动控制增强升力的方式已经被证明是最值得研究推广的应用技术之一。而在分析飞机起降性能时,必须要考虑到地面效应的影响,因此有必要对采用吹气进行增升的翼型地面效应进行研究。通过数值模拟方法研究了定常吹气对某无缝襟翼翼型地面效应的影响,研究表明,近地面在襟翼前缘施加吹气控制后,与远地面施加定常吹气控制相比,翼型升力线斜率和升力明显降低;小迎角下,动量系数为0.005时,升力随着距地高度的减小先减小后增加,动量系数增加到0.01后,升力随着距地高度的减小而减小;无缝襟翼翼型在不同动量系数和不同距地高度时出现的不同程度升力减小的现象,能直接影响飞机的起降性能,是采用吹气控制进行增升设计时必须考虑的因素。
As production costs, performance and reliability, and environmental requirements continue to increase, the future trend of transport aircraft is greater load, shorter take-off and landing distance, lower pollution emissions and noise, and there is an urgent need to adopt More efficient and simple ascent and control technology, and the use of active flow control of slit blowing to enhance the lift has proved to be the most worthy of research and promotion of one of the application technologies. However, when analyzing the take-off and landing performance of aircraft, it is necessary to consider the effect of the ground effect. Therefore, it is necessary to study the air-ground effect of airfoil with the increase of air blowing. The effect of constant blowing on the ground effect of a seamless flap airfoil was studied by means of numerical simulation. The results show that, compared with the conventional air blowing control, When the momentum coefficient is 0.005, the lift decreases first and then increases with the decrease of the height of the ground. When the momentum coefficient increases to 0.01, the lift decreases with the height of the ground And reduce; seamless flap airfoil in different momentum coefficient and different from the height of the ground when the phenomenon of varying degrees of reduced lift can have a direct impact on the take-off and landing performance of the aircraft is to use air-blowing control to increase the design must be considered the elements of.