FIELD: rocket engine. SUBSTANCE: nozzle has form of axial twin bell whose curvature changes outside or generatrices lie at point of maximum curvature between two bell forms. Change in curvature ranges from 2 to 7 deg for better cooling of nozzle wall; point of maximum curvature is located between section at ratio of area of ε = 10 and section at 0.85x0,85×εmax max of nozzle. EFFECT: improved cooling effect. 2 dwg
