1：Experimental Design and Method Selection:

The study used an experimental facility comprising a MAU-M supersonic wind tunnel and a repetitive pulsed CO2-laser to examine the effects of gas injection and pulsating optical discharge on aerodynamic drag. The aerodynamic force was measured using a single-component aerodynamic balance, and flow visualization was performed using the schlieren method.

2：Sample Selection and Data Sources:

A hemisphere-on-cylinder model of diameter 7 mm and length 25 mm was used, positioned at varying distances from the argon injection point in a supersonic air flow with Mach number M =

3：List of Experimental Equipment and Materials:

Equipment included a MAU-M supersonic wind tunnel, a repetitive pulsed CO2-laser, a single-component aerodynamic balance with CAS BCL-1L strain-gage sensors, TDM9-A pressure sensors, a ZnSe lens for laser focusing, an SCP-3200 recording system, a pulsed laser for schlieren visualization, TAL-100R telescopes, and a Videoscan-285P CCD video camera. Materials included air and argon gas.

4：Experimental Procedures and Operational Workflow:

The supersonic flow was established, argon was injected through a tube, and laser radiation was focused to create a pulsating optical discharge. The aerodynamic force on the model was measured under various conditions of laser power, pulse frequency, and model distance. Schlieren visualization captured flow patterns.

5：Data Analysis Methods:

Data from the aerodynamic balance and pressure sensors were recorded and analyzed to determine force reductions, with mean-square inaccuracies and systematic errors accounted for.