This paper describes the design, modeling, and analysis of an attitude control system for a ram-facing pico-class satellite in Low Earth Orbit (LEO). A 3-U (30×10×10 cm3) CubeSat is designed to maintain one 10×10 cm2 face aligned with the velocity vector throughout the orbit. The solution presented implements deployable drag fins and resembles a shuttlecock design which is shown to be capable of providing passive stabilization for orbits below 500 km. A simplified Direct Simulation Monte Carlo (DSMC) method is used to model the rarefied atmosphere and its interaction with the spacecraft body for a range of fin geometries. An attitude propagator is developed to observe the satellite's dynamic response and steady-state behavior considering perturbing torques due to gravity gradient and solar pressure. Stability characteristics and pointing errors are shown for altitudes ranging from 300 to 450 km with fin lengths from 2 to 30 cm at angles from 0 to 90 degrees.