Design of the Propelling Nozzles for the Launchers and Satellites

Authors: R. Haoui

Abstract:

The aim of this work is to determine the supersonic nozzle profiles used in propulsion, for the launchers or embarked with the satellites. This design has as a role firstly, to give a important propulsion, i.e. with uniform and parallel flow at exit, secondly to find a short length profiles without modification of the flow in the nozzle. The first elaborate program is used to determine the profile of divergent by using the characteristics method for an axisymmetric flow. The second program is conceived by using the finite volume method to determine and test the profile found connected to a convergent.

Keywords: Characteristic method, nozzles, supersonic flow, propellers.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1061166

References:

[1] Shapiro, A.H. (1954). The Dynamics and Thermodynamics of Compressible fluid flow. The Ronald Press Company, New York. Volume II. Ch.17.
[2] B. Van Leer, "Flux Vector Splitting for the Euler Equations," Lecture Notes in Physics. 170, (1982), 507-512.
[3] R. Haoui, A. Gahmousse, D. Zeitoun, " Chemical and vibrational nonequilibrium flow in a hypersonic axisymmetric nozzle (Ecoulement hors d-équilibre chimique et vibrationnel dans une tuyère hypersonique axisymétrique), " International Journal of Thermal Sciences, article n┬░ 8 , volume 40, (2001), pp787-795.
[4] R. Haoui, "Finite volumes analysis of a supersonic non-equilibrium flow around the axisymmetric blunt body," International Journal of Aeronautical and space Sciences, 11(2), (2010), pp59-68.
[5] R. Haoui, A. Gahmousse, D. Zeitoun, " Condition of convergence applied to an axisymmetric reactive flow (Condition de convergence appliquée ├á un écoulement réactif axisymétrique)," 16th CFM, n┬░738, Nice, France, 2003.