Results of theoretical researches of air intake in a rocket-basedt combined engine was present. Models of air inlet in the drive was consider at different number of air inlets and a variable corner of an air passage. Simulation of working process in a rocket-based combined engine are execute by a path of the solution of a set of equations of the Navier-Stokes describe flow of viscous compressible gas, a method of final volumes. Adequacy of computational models are show.
flow of gas, air inlet, speed, consumption, mixture, nozzle