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首页> 外文期刊>Journal of Propulsion and Power >Reduced-Order Modeling of Two-Dimensional Supersonic Flows with Applications to Scramjet Inlets
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Reduced-Order Modeling of Two-Dimensional Supersonic Flows with Applications to Scramjet Inlets

机译：二维超声速流的降阶建模及其在超燃冲压发动机进气道中的应用

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摘要

Control-oriented models of hypersonic vehicle propulsion systems require a reduced-order model of the scramjetninlet that is accurate to within 10% but requires less than a few seconds of computational time. To achieve this goal, anreduced-order model is presented, which predicts the solution of a steady two-dimensional supersonic flow throughnan inlet or around any other two-dimensional geometry. The model assumes that the flow is supersonic everywherenexcept in boundary layers and the regions near blunted leading edges. Expansion fans are modeled as a sequence ofndiscrete waves instead of a continuous pressure change. Of critical importance to the model is the ability to predict thenresults of multiple wave interactions rapidly. The rounded detached shock near a blunt leading edge is discretizednand replaced with three linear shocks. Boundary layers are approximated by displacing the flow by an empiricalnestimate of the displacement thickness. A scramjet inlet is considered as an example application. The predictednresults are compared to two-dimensional computational fluid dynamics solutions and experimental results.
机译：高超声速车辆推进系统的面向控制的模型需要超燃冲压进气口的降阶模型，该模型的精度必须在10％以内，但所需的计算时间少于几秒钟。为了实现这一目标，提出了降阶模型，该模型预测了通过南进口或任何其他二维几何形状的稳定二维超声速流动的解决方案。该模型假设流动是超音速的，除了边界层和钝边附近的区域。膨胀风扇被建模为一系列离散波，而不是连续的压力变化。对模型至关重要的是能够快速预测多次波相互作用的结果的能力。钝化前缘附近的圆形分离冲击被离散化，并被三个线性冲击所代替。通过用位移厚度的经验值来替代流，可以近似边界层。一个超燃冲压进气口被认为是一个示例应用。将预测结果与二维计算流体动力学解决方案和实验结果进行比较。

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