高超声速边界层转捩直接影响飞行器表面的摩擦系数与热流分布, 对于高超声速飞行器的气动
布局以及热防护设计至关重要. 尽管高超声速边界层层/湍流转捩的相关研究已经开展长达半个 …

Hypersonic reentry vehicles are subjected to high levels of fluctuating pressures. These
intense fluctuations can cause vibration of internal components and can lead to structural …

This study presents the experimental characterization of instability waves upon a hypersonic
laminar boundary layer of a flared-cone model using a nonintrusive optical diagnostic [that …

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 …

In this paper, we report on the application of the atomic layer thermopile (ALTP) heat-flux
sensor to the measurement of laminar-to-turbulent transition in a hypersonic flat-plate …

The stability of a three-dimensional hypersonic boundary layer is experimentally
investigated for a 7 deg half-angle cone at an angle of attack of 6 deg. The measurements …

Combined free-stream disturbance measurements and receptivity studies in hypersonic
wind tunnels were conducted by means of a slender wedge probe and direct numerical …

The development, validation, and introduction of physics-based approaches for stability and
transition prediction will lead to smaller and more manageable uncertainties in the design of …

Fast-response coaxial surface junction thermocouples have been used to measure time-
resolved stagnation temperature of the Mach 6 flow produced by the University of Southern …

The tunnel noise in a Mach 5.9 Ludwieg tube is determined by two methods, a newly
developed cone-probe-DNS method and a reliable hot-wire-Pitot-probe method. The new …