Effect of wall temperature on boundary layer transition prediction using transition model

The correct prediction of boundary layer transition is essential for a successful design of hypersonic flying vehicles. In this paper, the effect of wall temperature condition on boundary layer transition prediction using a transition model is studied. Modifications are made to the time scale based on non-turbulence kinetic energy and the production term of the intermittency factor equation of k-ω-γ transition model. The effects of wall temperature condition on the maximum amplification rate and critical Reynolds number are considered when modeling the first and second mode. The influence of wall temperature on a hypersonic boundary layer of a blunt cone with small nose bluntness at zero angle of attack is investigated by the modified k-ω-γ transition model. The improved model can provide reasonable results for the maximum amplification rate and the most unstable frequency of the first oblique and two-dimensional second mode both at adiabatic and isothermal wall conditions. The transition locations predicted by the modified k-ω-γ transition model agree well with those obtained by stability analysis.