The subject of this paper is numerical simulation of the Mach 6 flow-field over a flat plate. The plate is analysed under three conditions: cold, uniformly heated and non-uniformly heated. We identify the main five sources of experimental uncertainty, and use a sparse grid approach to build surrogates of the numerical results in order to propagate the input uncertainties to quantify the uncertainty in the numerical results, and to calculate Sobol' sensitivity indices of the numerical results with respect to the uncertain inputs. The numerical results correspond well to the experimental results when we impose laminar flow for the cold plate and turbulent flow for both heated plates. This suggests that the heating of the plate causes a transition in the boundary layer. The Sobol' indices indicate that the most influential experimental uncertainties are those of the far-field Mach number and the far-field temperature.
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