Effect of distributed gas injection on aerodynamic characteristics of a body of revolution in a supersonic flow

Results of experimental and numerical investigations of the effect of gas injection through a permeable porous surface on the drag coefficient of a cone-cylinder body of revolution in a supersonic flow with the Mach number range $\mathrm{M}_h=3–6$ are presented. It is demonstrated that gas injection through a porous nose cone with gas flow rates being $6$–$8\%$ of the free-stream flow rate in the mid-section leads to a decrease in the drag coefficient approximately by $5$–$7\%$. The contributions of the decrease in the drag force acting on the model forebody and of the increase in the base pressure to the total drag reduction are approximately identical. Gas injection through a porous base surface with the flow rate approximately equal to $1\%$ leads to a threefold increase in the base pressure and to a decrease in the drag coefficient. Gas injection through a porous base surface with the flow rate approximately equal to $5\%$ gives rise to a supersonic flow zone in the base region.