Local Wall Cooling Effects on Hypersonic Boundary-Layer Stability

Hypersonic boundary-layer stability has significant importance in vehicle design and successful operation. This paper investigates the stabilization effects of local wall cooling on hypersonic boundary layers over a 5 deg half-angle blunt cone with nose radius 0.0254 mm. We employed high-order-accurate flow solver to calculate steady for freestream Mach number 6.0 unit Reynolds [Formula: see text]. In simulations, we considered partial cooling, entire adiabatic scenarios. Furthermore, examined parameters such as strip location, length, temperature profiles. calculated growth rates, phase speed, text]-factor diagrams using linear analysis. The results showed that complete destabilizes layer. However, upstream synchronization point stabilized layer by damping disturbances. longer further placed downstream destabilized