Experiments are performed to investigate the effect of nose-tip bluntness on the instability
mechanisms leading to boundary-layer transition on a, the schlieren visualization region is …

边界层由层流向湍流的转捩是高超声速飞行器设计面临的重大空气动力学问题.
随着飞行速域与空域的不断拓展, 高超声速高焓边界层中的高温气体效应会使得量热完全气体 …

The existing database of transition measurements in hypersonic ground facilities has
established that as the nose-tip bluntness is increased the onset of boundary-layer transition …

Numerical and experimental studies have demonstrated laminar–turbulent transition in
hypersonic boundary layers over sharp cones via the modal growth of planar Mack-mode …

Visualization experiments are performed to investigate the development of instability waves
within the boundary layer on a slender cone under high Mach number conditions. The …

Boundary-layer transition was studied on a sharp 7 deg cone in two hypersonic wind tunnels
at Mach numbers of 5, 6, 8, and 14 over a range of freestream Reynolds numbers between …

The existing database of transition measurements in hypersonic ground facilities has
established that, as the nose-tip bluntness is increased, the onset of boundary-layer …

Hypersonic boundary-layer instability disturbance and transition experiments were
performed in the Air Force Research Laboratory Mach-6 Ludwieg Tube on a 1-m-long ogive …

Boundary layer transition from laminar to turbulence is of vital importance to the design of
hypersonic vehicles. With continuous expansion of flight speed and altitude domains, the …

View Video Presentation: https://doi. org/10.2514/6.2023-2438. vid A self-aligned focusing
schlieren (SAFS) apparatus based on a recently published design is implemented for the …