Deceleration of a supersonic flow down to transonic speeds using gas-dynamic pulses during combustion of hydrocarbon fuels

Creation of a transonic region by means gas fuel burning in supersonic flow with Mach number M = 2 channel variable cross section is studied numerically. The averaged Navier – Stokes equations closed the k-ε model turbulence are solved. created using gas-dynamic pulses throttling jet, which initiates gaseous combustion constant section. (ethylene or kerosene) supplied axially into axisymmetric channel. It shown that initiation kerosene requires higher power than those ethylene case. evolution process channels different lengths studied. pulse action duration required for increases length