In this paper, the flow field is investigated by solving the fluid dynamics and acoustics of the launch vehicle for a specific sample model with Fluent software. The model used in this research has been studied acoustically in one of the essays previously in the laboratory. The components that constitute the launch vehicle affect the level of noise exerted to the rocket as it rises. In the present study, an attempt is made to numerically examine the contribution of a component of the main launch structure, namely the launch pad, to the acoustics and the flow field around the known launch vehicle whose experimental information is available on a jet output current deflector. For this purpose, in order to ensure the numerical solution, the flow field of the fluid exiting the projectile jet was investigated in terms of pressure and flow velocity parameters as well as Mach number, which was in accordance with the experimental conditions presented in the experimental work. Then the acoustic power values were obtained as a contour on the current field symmetry plane by software. The size of the acoustic pressure level at the location of the sensors identified in the experimental work was determined in the present study and calculated according to the results of acoustic information. Comparison of acoustic results from numerical solution at near field sensors showed very close agreement in less than 3.3%. the difference is close to 8.9%, which is more than the near field results.