In this numerical work, three dimensional supersonic laminar flow and heat transfer of a blunt body(sphere-cone) at Mach 5 is simulated. The effects of angle of attack and the spin rate on the flow and heat transfer are analysed. To investigate the effect of angle of attack, computations are performed at constant angular velocity, 1000 rev/sec and the angle of attack is varied from 0° to 12°. To investigate the effect of the spin, the computations are carried out for the five cases of spin rate 0 rev/sec, 500 rev/sec, 1000 rev/sec, 1500 rev/sec and 2000 rev/sec at a constant angle of attack of 8°.
To solve the three dimensional compressible Navier-Stokes equation, a finite volume method with 2nd order AUSM scheme is employed for spatial derivatives, and a point SGS implicit method is employed for time integration.
It is found that the heat transfer at the windward and the right sides (viewed from the front) increases and the heat transfer at the leeward and left sides decreases with the angle of attack. The heat transfer rate at all surfaces, specially the windward and right sides increases as th spin rate increases.
