The design of solid rocket motors requires the prediction of changes induced by the ablation process occurring at the nozzle throat. The present study aims at understanding the effects of ablation on the turbulent boundary layer performing direct numerical simulations in a channel flow configuration. An ablation boundary condition for arbitrary chemical composition and pyrolysis scheme is developed and presented in this paper. Then, two DNS of a seven species reacting flow are performed: a) with inert walls; b) with ablated walls. Generated data are compared and analyzed looking at first order statistics. It is shown that the classical law of the wall for velocity and temperature are not appropriate to represent the numerical result. The chemical equilibrium assumption is shown to be valid in the inert case and a wall function consistent with this assumption is in fair agreement with the results.

No abstract