Ses üstü bir jetin aerodinamik ve aero akustik özelliklerinin numerik olarak incelemesi

In thesis scope, aerodynamic and aero-acoustic evaluations of a supersonic jet nozzle created and tested by NASA have been performed. Beside, by using AUSM+ method, a computer code and numeric method has been developed for 2D domain. In accomplishing study, aerodynamic and aero-acoustic investigations have been performed. In thesis, developed computer code and computational technics exists and also, the development process has been presented. Results obtained from numerical calculation have been compared to NASA's test results. As a result, from an aerodynamic point of view, results have correlated with test. However, from aero-acoustic perspective, due to the absence of turbulent and viscous terms, the results have not been correlated with the noise-frequency result. But, for shock noise band section trend appropriate with NASA's results. In conclusion, aerodynamic and aero-acoustic results and investigations have fulfilled.