We focus on the aerodynamic heating phenomenon occurring in the hypersonic region when a spacecraft enters the atmosphere of a planet (planet with the atmosphere such as the Earth and Mars), and the dynamic instability phenomenon related to the entry capsule when it decelerates from there to supersonic and transonic speed. For the former, we conduct research on measurement methods (including inverse problem solution methods) which can be used to estimate the aerodynamic heating which occurs on the body of the spacecraft directly with high precision using Temperature-Sensitive Paint (TSP). However, considerable problems remain in its measurement, and we will try to establish a new method which is more advanced than the current ones. We would also like to try to establish the database for spacecraft body design in fusion with CFD, in addition to measurement.

Research Topics

• Development of Measurement Technique for Aerodynamic Heating Rate on Hypersonic Flight Vehicle by TSP
• Visualization of Boundary Layer Transition Point on Hypersonic Flight Vehicle in Shock Wind Tonnel HIEST
• Study on Dynamic Unsteady Behavior of Re-entry Capsule in Transonic Flow