Numerical Investigation of New-Proposed Drag Reduction Technique for Hypersonic Flight

The most recent proposed technique for drag reduction in hypersonic flow speeds is using the exothermic coating on the blunt nose. This leads the heat addition into the flow field behind the shock wave, and increases the shock-stand-off distance. The variation of the drag force on the flying body using this technique is numerically investigated in the present study. The compressible turbulent flow is simulated around the body to compute the drag force, and to estimate the drag reduction capabilities of this technique. This quantitative analysis makes better insight to evaluate it in operational applications