ВЛИЯНИЕ ПОЛОЖЕНИЯ СКАЧКА УПЛОТНЕНИЯ НА ВЕЛИЧИНУ ТЯГИ ЖИДКОСТНОГО РАКЕТНОГО ДВИГАТЕЛЯ МАЛОЙ ТЯГИ ПРИ ИСПОЛЬЗОВАНИИ ЦИЛИНДРИЧЕСКОГО КОРМОВОГО ДИФФУЗОРА

Abstract

The article presents the numerical results of workflows in low-thrust liquid rocket engine when tested with a cylindrical diffuser. The graphs of the thrust dependence on the positionofshock wave wereobtained. The recommendations on the magnitude of the pressure at the exit from the cylindrical diffuser when performing high-altitude fire tests of the low-thrust liquid rocket engine were developedfor correctly determining the thrust of the engine.