Experimental and Numerical Investigation of Leading-Edge Bluntness on Shock Boundary layer Interaction Inside a Scramjet Inlet at Mach 6

This study investigates the impact of leading edge bluntness on the shock boundary layer interactions in scramjet intake at Mach 6 using numerical and experimental approaches. To investigate this bluntness radius varied from 0 to 1mm for both ramp and cowl leading edges. The numerical simulations show bluntness results in a significant increase in ramp and cowl nose tip pressure. Moreover, leading edge bluntness of 1.0 mm significantly changes the flow field in the isolator region, and the separation region exhibits a 43% increment in plateau pressure. Numerical simulations showed a good match with experimental values. The experimental results also suggest that a blunt leading edge significantly alters the flow field compared to a sharp leading edge. Additionally, unsteady pressure spectra analysis reveals a shift in shock and shear layer frequency towards the higher side and a reduction in frequency amplitudes with leading edge bluntness. This study highlights the importance of considering nose tip bluntness in the design and optimization of scramjet intakes, as it can play a crucial role in decreasing thermal loads and ensuring the aircraft's safety and durability.