Design of the Propelling Nozzles for the Launchers and Satellites

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.

Authors:

• R. Haoui

Keywords:

• Characteristic method
• nozzles
• supersonic flow
• propellers.

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.