Inverse problem of heat and mass transfer

The control law for ensuring the beforehand given local heat flow distribution (the condition for surface protection against heat destruction) from laminar boundary layer to the permeable surface is constructed for the hypersonic aircraft effusion heat protection mathematical modeling problem. The solvability questions in the cases of additional gas-dynamic restrictions (weak blowing) and/or constructive restrictions (impermeable insertions) are considered. The computational experiments results are discussed.