Significant industry interest in low-Reynolds number aerodynamics has made the assessment and comparison of computational methods with wind-tunnel experiments more compelling. Classical computational methods including XFOIL, MSES, and the Eppler program are compared along with OVERFLOW to newly published experimental data of a low Reynolds number airfoil, the PSU 94-097. At very low Reynolds numbers, all computational methods un-derpredict drag at lift coefficients occurring at the center part of the bucket. This general trend is likely due to difficulty in modeling laminar separation bubbles at low Reynolds numbers. At higher Reynolds numbers, the profile drag coefficient values are in great agreement. Predicted maximum lift coefficient, Cl,max, is overestimated by 0.3 for OVERFLOW and around 0.2 for XFOIL (version 6.94).