Effect of the fluidic injection on the flow of a converging-diverging conical nozzle

Razik Benderradji


The flow in an Over-Expanded Nozzle is subjected to shock waves leading to the unsteady separation of the boundary layer. Free detachment may be followed by a restricted detachment. During the expansion regime in propellant nozzles, several physical phenomena are encountered: supersonic jet, jet separation, adverse pressure gradient, shock wave, turbulent boundary layer, highly compressible mixture layer, return flow, large scale turbulence. These very complex phenomena can considerably affect the performance of the nozzle.The numerical investigation was performed by the CFD-FASTRAN search code, using the k-w SST model as the turbulence model. The calculation is performed by solving the Navier-Stokes equations of two-dimensional compressible turbulent flow. It is based on the study of the fluidic vectorization phenomenon of the thrust of a double-injection convergent-divergent supersonic conical nozzle. The study is based on the effect of the ratio of NPR pressures with SPR = 1 on the overall structure of shock waves. The calculation is highlighting the behavior of a flow that has not neglected. In particular, the appearance of the separation zone formed by the fluid jet and the deflection of the main jet cause separation shocks.

Full Text:



K. A. Waithe and K. A. Deere, “Experimental and computational investigation of multiple injection ports in a convergent-divergent nozzle for fluidic thrust vectoring”, 21st Applied Aerodynamics Conference, June, Orlando, Florida 2003.

F.W. Spaid, E.E. Zukoski, “Study of the interaction of gaseous jets from transverse slotswith supersonic external flows”, AIAA J.Vol 6, No 2, 1968, pp. 205–212.

Vladeta Zmijanovic, “Vectorisation fluidique de la poussée d'une tuyère axisymétrique supersonique par injection secondaire”, thèse de Doctorat, de l’Université d’Orléans, 2013.

V. Zmijanovic L. Leger, V. Lago, “Experimental and Numerical Study of Thrust Vectoring Effects by Transverse Gas Injection into a Propulsive Axisymmetric C-D Nozzle”, AIAA 2012-3874, 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 30 July - 01 August 2012, Atlanta, Georgia.

V. Zmijanovic, V. Lago, L. Leger, E. Depussay, M. Sellam, A. Chpoun, “Thrustvectoring effects of a transverse gas injection into a supersonic cross flow of an axisymmetric convergent-divergent nozzle”, progress in Propulsion Physics, Vol. 4, 2013, pp. 227-256.

N. Maarouf, M. Sellam, M. Grignon, and A. Chpoun, “Thrust vectoring through fluidinjection in an axisymmetrical supersonic nozzle: Theoretical and computational study”, Journal of shock wave, 2009; pp. 1142- 1146.

A. Ashraf, C. G. Rodriguez, A. J. Neely, and J. Young, “Combination of Fluidic Thrust Modulation and Vectoring in a 2D Nozzle”, AIAA 2012-3780, 48thAIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2012, Atlanta, Georgia.

Xin H. Zou, Qiang Wang, Hagemann, “The Comparative Analysis of Two Typical Fluidic Thrust Vectoring Exhaust Nozzles on Aerodynamic Characteristics”, World Academy of Science, Engineering and Technology Vol. 5, 2011, pp. 04-20.

Ahmed Remlaoui, Mohammed Benyoucef, Djamel Assi and Driss Nehari, “A TRNSYS dynamic simulation model for a parabolic trough solar thermal power plant”, International Journal of Energetica (IJECA),Vol 4. No 2. 2019.

DOI: http://dx.doi.org/10.47238/ijeca.v5i1.114


  • There are currently no refbacks.

Copyright (c) 2020 International Journal of Energetica

Creative Commons License
This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.

Creative Commons License
The content of this journal is licenced under a Creative Commons Attribution-NonCommercial 4.0 International License