Transonic Flow Field Analysis of a Minimum Nozzle Length Rocket Engine-Reference-Cited by-同舟云学术

Transonic Flow Field Analysis of a Minimum Nozzle Length Rocket Engine

Published:2024-06-10 Issue:2 Volume:16 Page:3-15
ISSN:2247-4528
Container-title:INCAS BULLETIN
language:en
Short-container-title:INCAS BULLETIN

Author:

ABADA Omar¹,KBAB Hakim²,HAIF Sidali²

Affiliation:

1. Aeronautical Sciences Laboratory, Institute of Aeronautics and Space Studies, University of Blida 1, BP 270 Blida 09000, Algeria, abadaomar@ymail.com

2. Aeronautical Sciences Laboratory, Institute of Aeronautics and Space Studies, University of Blida 1, BP 270 Blida 09000, Algeria

Abstract

The aim of this paper is to develop a profile of axisymmetric minimum length nozzle giving a uniform and parallel flow at the exit section. The study is done at high temperature, lower than the dissociation threshold of the molecules. The design is made by the method of characteristics (MOC). The variation of the specific heats with the temperature is considered. The numerical results have been validated with CFD simulation Ansys-Fluent software. The second part of this study is to calculate and analyze the transonic flow field of this supersonic nozzle. The computation of the flow field characteristics at the throat is thus essential to the nozzle developed thrust value and therefore to the aircraft or rocket it propels. An investigation was conducted to analyze the effects of parameters on the position of the sonic line. These parameters include stagnation temperature T0, radius of the nozzle, types of gases, and exit Mach number ME.

Publisher

INCAS - National Institute for Aerospace Research Elie Carafoli

Reference19 articles.

1. [1] C. R. Peterson and P. Hill, Mechanics and Thermodynamics of Propulsion, Addition, 1965.

2. [2] G. P. Sutton and O. Biblarz, Rocket propulsion elements. John Wiley & Sons, 2016.

3. [3] E. Truckenbrodt and E. Truckenbrodt, Elementare Strömungsvorgänge inkompressibler Fluide, Strömungsmechanik: Grundlagen und technische Anwendungen, pp. 152-261, 1968.

4. [4] G. I. Taylor, The flow of air at high speeds past curved surfaces, 1930.

5. [5] S. G. Hooker, The Flow of a Compressible Liquid in the Neighbourhood of the Throat of a Constriction in a Circular Wind Channel, Proceedings of the Royal Society of London, Series A, Containing Papers of a Mathematical and Physical Character, vol. 135, no. 827, pp. 498-511, 1932.