Stability analysis and transition prediction of hypersonic boundary layer over a blunt cone with small nose bluntness at zero angle of attack

摘要: Stability and transition prediction of hypersonic boundary layer on a blunt cone with small nose bluntness at zero angle attack was investigated. The radius the is 0.5 mm; half-angle 5°, Mach number oncoming flow 6. base obtained by direct numerical simulation. linear stability theory applied for analysis first mode second unstable waves under both isothermal adiabatic wall condition, eN method used location. N factor tentatively taken as 10, no experimentally confirmed value available. It found that temperature condition has great effect For wall, would take place more rearward than those wall. And despite high flows, maximum amplification rate wave far bigger wave, location controlled growth waves. methods employed in this paper are expected to be also applicable three dimensional layers cones attack.