In this study, a trajectory simulation is developed in order to estimate pre-apogee flight parameters of low altitude rockets. It is intended to evolve a mathematical model of trajectory of rocket and provide a perspective for design and performance analysis. The rocket's equations of motion of are integrated using the fourth-order Runge-Kutta method. First, the variation of altitude, velocity, acceleration, and pitch angle values of the rocket with time during flight are investigated. Secondly, the center of pressure and center of gravity are dynamically calculated to determine changes in the rocket's static margin during flight. This approach allows the simulation to provide information regarding the stability of the rocket. The accuracy of the numerical results is verified by comparing them to real flight data and an open source software. For this purpose, two rockets with design parameters and real flight data, previously launched to different altitudes, are used in the study. This research specifically focuses on orbital simulation and stability of unguided, low-altitude, subsonic sounding rockets and highlights the importance of modeling and simulation in the design and optimization of rockets. [ABSTRACT FROM AUTHOR]