A method of calculating the flow around and aerodynamic design of the profiles of turbomachinery blade grids
The author applies an iterative method for optimization of turbomachine cascade profile. A special attention is paid to boundary conditions for the potential equation in the curvilinear coordinates and to the choice of difference approximations. For solution of the obtained nonlinear difference system a linearization is used with inner iterations involving factorized grid operators. Numerical examples are presented.
scientific article; zbMATH DE number 220265