|Abstract:||Small satellites, such as CubeSats and SmallSats, are seeing increased use in Low Earth Orbit, particularly at altitudes with measurable aerodynamic effects. It is important to design these spacecraft, which often have modest control authority, such that the resultant aerodynamic forces and moments do not cause unstable motion, which may lead to premature loss of mission. Building from free molecular pressure and shear equations for flat plates, an aerodynamic solver is designed to analyze the aerodynamic forces and moments on a 3U CubeSat with center of gravity offset, orbiting at altitudes from 80 to 200 km. The motion of this CubeSat is then simulated for a variety of initial conditions, both with and without active control, to determine its behavior. Inferences are made as to design rules that will lead to more stable small satellites.