Aerodynamics provide a small but significant effect on the dynamics of vehicles operating in low Earth orbit, especially CubeSats with limited control authority. Current analysis tools treat the translational and attitude dynamics of these vehicles in a decoupled sense. A coupling of these effects provides a more holistic view of the problem. In this work, various control system and physical properties of CubeSats are compared based on metrics of detumble time, total mission lifetime, and ram-pointing effectiveness. The control systems used are a magne-torquer with either a simplified Bcross detumble algorithm or a Quaternion Rate Feedback (QRF) pointing algorithm, or a set of reaction wheels using QRF. The physical properties examined are the total available control effort, the initial apoapsis of the orbit, the duty cycle of the control system, and the percent of eclipse in which control is active. Results indicate that a vehicle equipped with the Bcross algorithm will have limited pointing performance which limits the mission lifetime, while reaction wheels using QRF are capable of asymptotic stability around the ram direction, and magnetorquers using the same algorithm are able to provide nearly the same total mission duration, at a cost of worse pointing acquisition time.