To measure heat flux on the sharp leading edge and other surface with very small curvature radius in the wind tunnel, Hong-Ru Yu proposed a novel design of integral type heat flux sensor. Compared with the traditional heat flux sensor, the integral type heat flux sensor improved spatial resolution up to an order of magnitude, and the size of the sensing elements has been minimized to 0.1 mm successfully, which satisfied the heat flux measurement requirements at R0.5 mm pointed cone stagnation point. A constantan film was used as the contact layer of the integral heat flux sensor, which was prepared by electron beam co-evaporation method. The influence of sensor structure on the accuracy of measurement was analyzed using numerical calculation. The measurement results in shock wave wind tunnel indicated that the response frequency was about 100 kHz and the repeatability error was less than 10 %.

In our previous study, the transition behavior of a flared cone–swept fin configuration was investigated under an angle of attack (AoA) of 0°. To further explore the role of AoA in complex three-dimensional geometries with strong fin–body interactions, wind tunnel experiments were conducted at Ma = 9.3, Re = 1.36 × 10⁷/m, with AoA ranging from −6° to 6°. Global surface temperature distributions were obtained using temperature-sensitive paint (TSP), while localized heat flux and pressure fluctuations were captured using thin-film thermocouples and high-frequency pressure sensors. The results show that varying AoA shifts the location of high heat flux between the upper and lower surfaces of the flared cone and induces a switch from streamwise to separation vortices. The windward side exhibits stronger disturbance responses than the leeward side. The junction region between the flared cone and the near-horizontal surface is highly sensitive to AoA variations, consistently exhibiting pronounced second-mode instabilities. These findings provide experimental support for understanding transition mechanisms under the combined effects of shock/boundary layer interaction (SBLI), crossflow, and adverse pressure gradients, with implications for transition prediction and thermal protection system design.