The present study numerically and experimentally investigates the flow characteristics and shock wave interactions produced by dual jet injection placed in tandem with each other in the streamwise direction into a supersonic cross flow of Mach 2.2. It was seen that the first jet (IJ1) which is located upstream of the second jet (IJ2) splits into two parts and wraps around the IJ2. The IJ1 and IJ2 wrap and twist around each other due to the presence of the counter-rotating vortex pair created by the second jet. Numerical schlieren and iso-contours of density revealed that the shock wave structures and their reflections produced due to tandem injection are quite different from a typical single transverse jet in a supersonic crossflow. It was found that the shock structures (Mach disk and bow shock) produced by the downstream jet are primarily influenced by the upstream jet. These findings will provide valuable insight into designing a tandem fuel injection system for a scramjet combustor.