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针对由后掠侧压进气道、矩形燃烧室和后掠侧板尾喷管构成的超燃冲压发动机模型,为了快速准确得到超燃冲压发动机的整机性能,建立了一套分析发动机总体性能的耦合流场计算方法。其中进气道和尾喷管流场分别求解三维单一气体和多组分抛物化N-S方程,燃烧室流场求解一维N-S方程,各部件在交接面处传递几何和流动参数。运用总体性能计算方法,研究了发动机构型的气动特性,给出了飞行高度、马赫数和攻角改变对发动机性能的影响规律。结果表明:该总体性能计算方法可用于超燃冲压发动机总体性能的快速预估;飞行高度对推力、升力和俯仰力矩的影响均较大且程度相近,三者随飞行高度增加均减小;飞行马赫数对发动机推力、升力的影响相近,对俯仰力矩的影响最大,三者随飞行马赫数增加均增加;飞行攻角对升力的影响最大,俯仰力矩次之,对推力的影响最小,随飞行攻角增加,发动机升力近似线性增加,推力和俯仰力矩分别呈增加和减小趋势。
For the scramjet engine model composed of the swept side inlet, the rectangular combustor and the tail-swept side-tail nozzle, in order to get the whole performance of the scramjet quickly and accurately, a set of method to analyze the overall performance of the engine Coupled flow field calculation method. The three-dimensional single-gas and multi-component parabolic N-S equations are solved in the inlet and tail nozzle flow fields respectively. The one-dimensional N-S equation is solved in the flow field of the combustor. The geometrical and flow parameters of each component are transferred at the interface. The aerodynamic characteristics of the engine configuration are studied by using the general performance calculation method. The influences of flight altitude, Mach number and angle of attack on the performance of the engine are given. The results show that this method can be used to predict the overall performance of scramjet. The effects of flight altitude on thrust, lift and pitching moments are both larger and similar, and all three decrease with the increase of flight altitude. The Mach number has the similar effect on the thrust and lift of the engine and has the greatest influence on the pitching moment. The three increase with the increase of flight Mach number. The attack angle of attack has the most influence on the lift and the pitching moment has the least impact on the thrust. As the angle of attack increases, the engine lift increases approximately linearly, and the thrust and pitch moments increase and decrease, respectively.