Aerodynamic Heating and Characteristics in Hypersonic Flow

High Enthalpy Shock Tunnel (HIEST) can make the most nearest flow to re-entry conditions of high enthalpy and high Reynolds number. We also own the high accuracy measurement tecnique specilizes in super short test duration of HIEST. We are conducting experiments of aerodynamic heating and aerodynamic characteristics of hypersonic flying bodies (Collaborative Research wiith NASA) by using these high-performance wind tonnel and measurement tecnique.

Turbulent Flow Heat Flux Measurement of Apollo Capsule

For the development of hypersonic cruiser using the scramjet engine, the evaluation of the entire model including the engine is necessary because aerodynamic characteristics of body and engine performance interact. Our laboratory developed the model, which exceeds 1 m, of hypersonic cruiser with engine and has evaluated aerodynamic performance of entire cruiser. We are also conducting the collaborate research (DLR) on boundary layer transition in hypersonic flow which effects aerodynamic characteristics.

JAXA Kakuda Space Center

Our Laboratory researches in JAXA Kakuda Space Center which leads development in rocket engines. Lately the center is also developing a future compound engine and performes experiments of atomospheric re-entry.

Spacecraft Thermal and Fluids Systems Laboratory

Our laboratory is collaborating with Spacecraft Thermal and Fluids Systems Laboratory, Institute of Fluid Science, Tohoku University.