[1]
Ю. М. Терещенко, В. М. Дихановський, Л. Г. Волянська, and О. В. Юрченко, “Quasi-spatial method for finding optimal design angles for the entrance and exit of blade crowns of the axial compressor of a gas turbine engine”, Proceedings of National Aviation University, vol. 11, no. 4, pp. 30–34, Jan. 2020.