INFLUENCE OF INJECTION OF THE THERMAL SHIELD DECOMPOSITION PRODUCTS ON THE FLOW COEFFICIENT OF A RECESSED NOZZLE DEPENDING ON THE INLET SECTION SHAPE

The infl uence of injection of the products of ablation of a heat-shielding coating of a recessed nozzle with the inlet section of radial and ellipsoidal shape on the fl ow coeffi cient of a solid propellant rocket engine has been estimated. The studies were carried out by the modern methods of computational fl uid dynamics in a quasistationary formulation. The boundaries of the change in the fl ow coeffi cient depending on the intensity of injection of decomposition products into the main fl ow are determined in accordance with the change in the heat fl ux to the surface of the heat-shielding coating. The infl uence of the shape of the inlet section, its geometric parameters, and of the temperature of decomposition products on the fl ow coeffi cient is shown.
   
Author:  A. N. Kirillova, A. N. Sabirzyanov
Keywords:  solid-propellant rocket engine, recessed nozzle, heat fl ux, injection of ablation products, fl ow coeffi cient, computational fl uid dynamics
Page:  1248