This paper consists of an evaluation of Computational Fluid Dynamic (CFD) simulations for supersonic jets operating off-design with corresponding experiments. It is part of an ongoing project to predict Broadband Shock Associated Noise (BBSAN). Axisymmetric steady state CFD results are produced with a Reynolds Averaged Navier-Stokes solver using a two equation turbulence model. These results are directly compared with experimental results for two different axisymmetric nozzles operating over- and under-expanded. Profiles of Pitot pressure and static pressure probes form the basis for evaluating Mach number and local static pressure at various downstream locations. Both experimental and numerical schlieren are compared side by side for a qualitative assessment of the accuracy of the flowfield predictions. Numerical and experimental contour plots are produced for further analysis. Finally, CFD results are verified further by demonstrating how the shock noise source strength varies with the off-design parameter in preparation for the BBSAN model development.