As a typical projectile with high spinning speed was taken as an example

the flight data of the projectile at supersonic

transonic and subsonic states were separately defined as the inflow conditions

and the fluid-thermal analysis was simulated by a combination of sliding mesh and multi-coordinate approaches. The coupling implicit algorithms based on density

Roe-FDS （flux difference splitting） flux scheme and SST (shear stress transfer) k -ω turbulence were also applied in simulations. The pressure

temperature

density

heat flux and turbulent kinetic energy on the surface of the flight body with high spinning speed were studied

and compared with the flow field disregarding the spinning speed. Results demonstrated that the streamlines interfered with each other

and disturbance of the airflow on the surface of the was more intense under the spinning conditions. Moreover

airflow accumulations at the tail of the were obvious

and the development and evolution of turbulence were more complicated. The velocity

pressure

temperature

and heat flux on the surface of the flight body were higher than those disregarding the spinning speed

especially at supersonic regimes.