arXiv subjects

Kiyoshi Kinefuchi

Publications and source records attributed to Kiyoshi Kinefuchi.

3 recordsLinked to original sources

arXiv2026

Wall heat transfer and flow field configuration of shock wave-turbulent boundary layer interactions on cryogenically cooled wall

In this study, we experimentally investigated the wall heat transfer and flow field configuration of incident-reflected shock wave-turbulent boundary layer interactions on a cooled wall in supersonic flow. Wind tunnel experiments were conducted at a Mach number of 2.0 and a total temperature of 289 K. To create a cooled-wall state, the wind tunnel wall was cooled to a cryogenic temperature using liquid nitrogen at 77.4 K. In addition to conventional measurements, such as the schlieren visualization method and pressure measurements, cryogenic temperature-sensitive paint was employed to clarify the relationship between the flow field configuration and wall heat flux on a cryogenically cooled wall. The wall surface temperature of the cryogenically cooled wall was 95 K, corresponding to a wall-to-recovery temperature ratio of 0.34. The oil flow image and wall surface temperature distribution indicated a quasi-two-dimensional flow at the center of the wind tunnel. The schlieren images and wall pressure distributions showed that the separation point under the cooled-wall condition shifted downstream compared with that under the uncooled-wall condition. Based on the temperature distribution obtained from the cooled-wall experiments, the wall heat flux at the separation point reduced due to the outward flow from the wall. The peak wall pressure ratio and wall heat flux ratio normalized by their upstream values exhibited trends consistent with previously reported data under the cooled-wall condition. These results suggest that the cryogenic temperature-sensitive paint is a powerful tool for investigating the effects of wall temperature on the shock wave-turbulent boundary layer interactions on cryogenically cooled walls.

physics.flu-dyn↗

arXiv2025

Visualization of Suppressed Shock Wave/Turbulent Boundary Layer Interaction Using Cryogenic Wall Cooling

To investigate the wall-cooling effects on shock wave turbulent/boundary layer interaction (SWTBLI) with limited experimental data, a supersonic wind tunnel wall was cooled using liquid nitrogen as the cryogenic coolant. Under the condition of the mainstream Mach number, in the range of 2.02-2.04, the wall temperature was cooled to 88-92 K, corresponding to a wall-to-recovery temperature ratio of 0.31-0.33. The flow structures with and without wall cooling were observed using the schlieren method. The reflected shock motion or interaction length in the schlieren image suggested that boundary layer separation was suppressed under the cooling condition in relation to that under the non-cooling condition, and the suppressed ratio of the cooling-to-uncooling interaction length was approximately 0.60-0.72. Additionally, while the mainstream state and wall temperature near the separation were constant, a gradual change in the separated flow field was observed under the wall-cooling condition. This was due to the slow wall temperature increase in the upstream wall of the separation region, where the incoming boundary layer developed. Each flow field of SWTBLI in the present experiment, using liquid nitrogen as the cryogenic coolant, was consistent with the classical Chaman's free interaction theory.

physics.flu-dyn↗

arXiv2018

Numerical investigation of nanosecond pulsed plasma actuators for control of shock-wave/boundary-layer separation

This study numerically explores the flow physics associated with nanosecond pulsed plasma actuators to control shock-wave induced boundary-layer separation. By using two actuators, parallel and canted with respect to the main flow direction, a previous experiment suggested the actuator worked in two ways: boundary layer heating and vorticity production. The heating effect was enhanced with the parallel electrode and made the separation stronger, while the canted electrode produced vorticity and suppressed the separation due to the momentum transfer. Because the detailed physics is still unclear, a numerical investigation is undertaken with a large eddy simulation and an energy deposition model for the actuator. The flow without the actuation corresponds to the experimental observation, indicating the calculation successfully resolves the separation. With the actuation, as with the experiment, the calculation successfully demonstrates definite difference between the parallel and canted electrodes: the parallel electrode causes excess heating and increases the separation, while the canted electrode leads to a reduction of the separation, with a corresponding thinning of the boundary layer due to the momentum transfer. The counter flow created by the canted actuator plays an important role in the vortex generation, transferring momentum to the boundary layer and, consequently, mitigating the separation.

physics.flu-dyn↗