Multi-channel maximum thrust combined nozzle design method based on supersonic shear layer modeling and supersonic shear layer modeling algorithm

The invention firstly discloses a supersonic shear layer modeling algorithm, which comprises the following steps of: selecting airflow pressure and airflow angle as iteration variables, and continuously iterating by adopting a pre-estimation-correction method based on aerodynamic parameters of known points in a discrete flow field until the relative error between the iteration variables is smaller than a preset threshold value, and converging the iteration variables; solving a supersonic shear layer point based on the estimation-correction thought; meanwhile, the invention further provides a multi-channel maximum thrust combined nozzle design method based on the supersonic shear layer modeling algorithm. Comprising the steps of upstream channel I and channel II inverse design solution, initial value surface downstream mixing section flow field solution, shear layer modeling solution, nozzle tail nozzle wall surface coordinate solution, maximum thrust nozzle control point solution and maximum thrust nozzle con