This study presents a computational aerodynamic model for sounding rockets based on the combination of the panel method and theoretical and semi-empirical formulae. The advantages of this model include low cost and the capability of working on a wide range of the Mach number. The reliability of the model was verified by comparing the computational results with data from supersonic wind tunnel experiments. Using the present computational model, the authors have studied the aerodynamic characteristics of a sounding rocket in the range of Mach number from 0 to 4. The study also proposes a method to calculate the aerodynamic coefficients in the unsteady case.