The base drag of axisymmetric bodies at supersonic speeds make a substantial contribution to the total drag. We employed computational fluid dynamics for investigating transitional supersonic axisymmetric wakes at a freestream Mach number of M = 2.46. The objective of this research is to study how various active and passive flow control techniques affect the base drag and to understand how the mean flow properties are altered by these techniques. Simulations were carried out for a Reynolds number based on diameter of Re D = 100, 000. To lower the grid resolution requirements and save computer time we employed a hybrid turbulence model, the flow simulation methodology. We investigated flow control mechanisms that alter the near wake by introducing axisymmetric and longitudinal perturbations in the approach boundary layer. We also investigated passive control using steady bleed jets.