This experimental work concerns the ability to modify the bow shock of a Soyuz-type model with an MHD actuator in supersonic and low-density plasma flows. A neodynium magnet inserted into the model creates a magnetic shield on the front side of the model. For comparison, an identical model is used to analyse the generic shock wave under similar operating conditions. Visualization and analysis of the shock wave shape was performed using images of the flow field obtained with an iCCD camera. The temperature of the wall model was measured simultaneously with an IR thermal camera. To investigate the influence of the plasma chemical composition, measurements were made in argon and air plasma streams. The results show that the MHD actuator increases the thickening and distance of the shock wave. The wall temperature of the model is therefore also changed. The rate of temperature increase is slower, which leads to lower values for the maximum temperature reached. Nevertheless, differences were observed depending on the nature of the chemical plasma.