Condensation of water vapor and carbon dioxide in the jet exhausts of rocket engines: 1. Heterogeneous condensation of combustion products

• Published in: Geomagnetism and Aeronomy Vol. 54; no. 1; pp. 104 - 108
• Main Authors: Platov, Yu. V., Semenov, A. I., Filippov, B. V.
• Format: Journal Article
• Language: English
• Published: Boston Springer US 2014; Springer Nature B.V
• Subjects: Aeronomy; Earth and Environmental Science; Earth Sciences; Geophysics/Geodesy; Jet engines; Rockets; Rocket Engine; Combustion Product; Water Vapor Condensation; Radiation Energy Loss; Water Vapor
• ISSN: 0016-7932; 1555-645X; 0016-7940
• DOI: 10.1134/S0016793214010125

Condensation of water vapor and carbon dioxide in the jet exhausts of rocket engines during last stages of Proton, Molniya, and Start launchers operating in the upper atmospheric with different types of fuels is considered. Particle heating is taken into account with emission of latent heat of condensation and energy loss due to radiation and heat exchange with combustion products. Using the solution of the heat balance and condensed particle mass equations, the temporal change in the temperature and thickness of the condensate layer is obtained. Practically, no condensation of water vapor and carbon dioxide in the jet exhaust of a Start launcher occurs. In plumes of Proton and Molniya launchers, the condensation of water vapor and carbon dioxide can start at distances of 120–170 m and 450–650 m from the engine nozzle, respectively. In the course of condensation, the thickness of the “water” layer on particles can exceed 100 Å, and the thickness of carbon dioxide can exceed 60 Å.