One major aspect of wind tunnel measurements is the influence of test section walls on the measured data. In this paper, a numerical investigation of the supersonic flow around a conventional missile configuration is conducted. Wall effects are addressed by comparing two computational domains, unbounded and bounded. The calculated aerodynamic coefficients are compared with own corresponding measured values. The results show a good agreement between the measured parameters and those derived from the bounded computational domain. The impact of the walls on the flow field structure is investigated by comparing the bounded and unbounded numerical simulations.