This research develops a dynamics and control framework for an unmanned powered parachute system. The 6 DOF dynamics are derived from the first principle/fundamentals. The dynamic equations are simulated and validated within the MATLAB Simulink simulation environment. A Model Reference Adaptive Controller algorithm is utilized and simulated to update coefficients to control the plant more accurately. A Computational Fluid Dynamics (CFD) simulation using SimScale is used to estimate aerodynamic coefficients. This paper is presented as a building block/work in progress for future work on robust and efficient adaptive control of powered parachute aerial vehicles. Derivation of the dynamic equations is included in section two, while section three covers methods used to computationally define key aerodynamic coefficients and describe PPC simulation within the MATLAB Simulink environment. Finally, section four presents the results. Further research into this framework will include validating results through experimentation of the PPC aircraft and comparing dynamic model accuracy. Finally, more advanced control techniques will be applied to the PPC model in simulations and experiments.