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为了能在双模态超燃冲压发动机流道方案初步论证中提供一种较快速的发动机性能计算方法,在二维N-S方程基础上,引入一维完全燃烧计算方法,提出了预估超燃冲压发动机性能的准二维计算方法。该方法能够计入激波、边界层分离等对发动机性能的影响,可在较短时间计算出整机推力、比冲性能和沿程热力学参数。通过对自由射流发动机计算,验证了此方法。并在此基础上,初步分析了燃料喷注位置和流道构型对发动机性能的影响。
In order to provide a fast calculation method of engine performance in the preliminary demonstration of bimodal scramjet engine runner program, based on the two-dimensional Navier-Stokes equations, a one-dimensional complete combustion calculation method is introduced and the prediction of scramjet Quasi two dimensional calculation method of engine performance. This method can account for the influence of shock wave and boundary layer separation on the engine performance, and can calculate the thrust, specific impulse and thermodynamic parameters of the whole machine in a relatively short period of time. This method is validated by calculating the free jet engine. Based on this, the influence of fuel injection position and runner configuration on engine performance is analyzed.