Permeable surfaces hypersonic aircraft optimal heat protection mathematical modeling

The problems of intended for the atmosphere entry hypersonic aircraft surfaces optimal effusion heat protection mathematical modeling are considered. The physico-chemical processes (the dissociation and the ionization) in laminar boundary layer of compressible gas are appreciated. The Groups theory approach to distributed parameters systems optimization is applied. An optimal control in the first approximation in analytical form is obtained. Some possibilities of special blow laws use for hypersonic aircraft surfaces heat protection nearing to optimal are considered. Computation experiments numerical results are discussed.