Hypersonic Boundary-Layer Transition Lab

On a hypersonic vehicle's forebody, the boundary layer starts out smooth and laminar at the nose but rarely stays that way — a resonant acoustic disturbance called the Mack second mode grows exponentially downstream until the flow breaks down into turbulence, multiplying the local heat flux the thermal-protection system must survive. This simulator renders that process on a slender 3D body using the industry-standard e^N transition-prediction framework in simplified form: adjust Mach number, wall cooling, unit Reynolds number and environment noise to watch the amplification factor N(x) climb along a live graph, tracer particles shift from laminar blue through amplifying amber to turbulent red, and the transition front move forward or aft exactly as it does on real hypersonic vehicle design charts.