Abstract
A numerical construction is proposed for the shape of the wall of the subsonic part of a nozzle. The design realizes nonseparated flow with an absence of local supersonic zones. The method is based on the simultaneous numerical solution of boundary-layer equations and equations of motion of an inviscid gas.
Similar content being viewed by others
Literature cited
I. L. Osipov, “Numerical method of designing plane nozzles,” Izv. Akad. Nauk SSSR, Mekh. Zhidk. Gaza, No. 2, 179–183 (1979).
A. P. Byrkin and V. V. Shchennikov, “Numerical method of calculating a laminar boundary layer,” Zh. Vychisl. Mat. Mat. Fiz.,10, No. 1, 124–131 (1970).
G.-G. Borger, “Optimierung von Windkanaldusen fur den Unterschallbereich,” Z. Flugwiss.,23, No. 2, 45–50 (1975).
J. Anderson, Gas-Discharge Lasers [Russian translation], Mir, Moscow (1979).
G. Schlichting, Boundary Layer Theory, McGraw-Hill.
Author information
Authors and Affiliations
Additional information
Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 42, No. 5, pp. 724–729, May, 1982.
Rights and permissions
About this article
Cite this article
Osipov, I.L., Shipilin, A.V. & Shulishnina, N.P. Shape of the subsonic part of a nozzle with a flat acoustic surface with allowance for viscosity in the boundary-layer approximation. Journal of Engineering Physics 42, 491–495 (1982). https://doi.org/10.1007/BF00824937
Received:
Issue Date:
DOI: https://doi.org/10.1007/BF00824937