One of the objectives of the RANGE mission is to perform relative navigation using differential aerodynamics. The aerodynamic force coefficients, moment coefficients, and heating can be computed numerically, though this process is too computationally expensive to integrate directly into an orbit propagator. A surrogate model is developed to improve the modeling fidelity beyond a simple sphere or plate model without significantly increasing computational cost. The training points for this model come from an industry standard code for Direct Simulation Monte Carlo analysis. Detailed discussions of model development, validation, and results are included.