Heat and mass transfer taking place in a case when thermal-protective composites are exposed intensive aeration in conditions of gasdynamic heating of hypersonic aircrafts is modeling. Conditions of origination, velocity of movement and coordinates of the zone of decomposition of the binder with origination gaseous products of decomposition and porous carbon residue, which pyrolized gases are filtering through toward an external boundary and injected into a high temperature boundary layer, are defined. This filtration is possible in the conditions when the stagnation pressure of pyrolized gases in the pyrolysis zone is higher than the pressure in a gasdynamic flow on the external boundary. Nonsteady temperature fields in both phases, mass velocity of the pyrolisys zone movement, mass velocity gas formation, stagnation pressure of gases in the pyrolysis zone and distribution of the filtration pressure in a porous residue and possible gap of the porous residue under exposure to tension from the pressure in the pyrolysis zone are defined.