In this study, density gradients were visualized using Z-type schlieren to analyze shock/shock interactions and the deviation of flow structure from the ideal gas assumption, taking into account the size of the first Mach disk, Prandtl–Meyer angle at the nozzle exit, and the existence and strength of the shock plate. Three different nozzle pressure ratios (NPR = 5, 9, 14) were examined as the nozzle static inlet temperature dropped from 290 K to cryogenic levels at 178 K. A significant difference in the flow structure of the jet near the impingement surface has been seen as the static inlet temperature drops from ambient temperature (290 K) to cryogenic conditions (178 K). Considering the inlet static temperature drop from 290 to 178 K, a 30% increase in mass flow rate exists at the throat for all NPRs. Furthermore, the impingement loads have been measured for different NPR concerning the temperature, showing that the loads affecting the spherical obstacle at Tin = 290 K are higher than that at Tin = 178 K.