Numerical Study of Viscous Flows in Rocket Engine Nozzles with an Optimized Supersonic Part and Separation of the Laminar Boundary Layer from the Wall

• Published in: Russian aeronautics Vol. 65; no. 4; pp. 799 - 809
• Main Authors: Kryukov, I. A., Ivanov, I. E., Shustov, S. A.
• Format: Journal Article
• Language: English
• Published: Moscow Pleiades Publishing 01-10-2022; Springer Nature B.V
• Subjects: Aircraft and Rocket Engine Theory; Automotive Engineering; Engineering; Gas flow; Laminar boundary layer; Liquid propellant rocket engines; Liquid propellants; Nozzles; Pressure ratio; Separation; Software; Thrust; Viscous flow; nozzle; gas-dynamic flow; rocket engine; Navier–Stokes system of equations; laminar regime; separation of the boundary layer from the wall
• ISSN: 1068-7998; 1934-7901
• DOI: 10.3103/S1068799822040213

The aim of this work is the development of computational tools based on the solution of the system of Navier–Stokes equations for numerical study of viscous gas flows in the nozzles of liquid propellant rocket engines with a thrust optimized contour of the supersonic part with separation of the laminar boundary layer from the wall. The energy and thrust characteristics of these engines are determined for the flow with separation in the nozzle for a wide range of nozzle pressure ratio.