Laminar to turbulent transition in supersonic boundary layer is numerically investigated by combining linear stability theory and Uncertainty Quantification. Linear stability theory is used to determine the N-factor for the e~N transition prediction method for a Mach 6 flat plate test case. Transition onset location is determined by using the N-factor experimentally obtained in the facility where the test was carried out. Uncertainty quantification is used to compute the probability of transition within the intermittency region downstream of the transition onset. The stochastic approach allows to model the transition region as in the experimental cases since a gradual passage from the laminar to the turbulent flow is obtained. The probability of transition resembles the shape of the skin friction or the heat flux distribution generally observed in the experiments within the transition region. Here we focus on the transition zone rather than on the onset location.
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