Results 1 to 10 of about 678 (224)

Numerical method for calculating the nozzle thrust of a wide-range rocket engine [PDF]

Научно-технический вестник информационных технологий, механики и оптики, 2022
A numerical method for calculating the thrust of a wide-range rocket engine nozzle has been developed. This type of engine is equipped with an annular nozzle with a flat central body and is designed to operate in the upper atmosphere and in vacuum.
A. A. Kirshina, A. A. Levikhin, A. Yu. Kirshin   +2 more
doaj   +2 more sources

Advanced Computational Flow Analysis - Rocket Engine Nozzle

Asian Journal of Research in Social Sciences and Humanities, 2016
Analysed a rocket engine nozzle to understand the phenomena of various design conditions under the different convergent angle, divergent angle and throat radius by Computational Fluid Dynamics (CFD). Convergence problems regarding rocket nozzle is analysed in different angles.
S. Senthil Kumar, M. Arularasu
openaire   +2 more sources

CONTOUR DESIGN FOR SOLID-PROPELLANT ROCKET-ENGINE NOZZLE

Journal of Science and Technique, 2020
In this paper, the characteristic line method is used to establish the equation describing the nozzle diverging contour. The converging contour of the nozzle is built according to the Witoszynski formula. Numerical calculation is applied to the 9M22Y uncontrolled rocket.
Minh Phu Nguyen
openaire   +3 more sources

CFD Analysis of De Laval Nozzle of a Hybrid Rocket Engine [PDF]

E3S Web of Conferences
: The study gives a general overview of the CFD-simulated gas flow via the nozzle of a De Laval rocket engine. In CFD software, the mesh is generated using the nozzle’s geometry.
Ahmad Mohamed Tarmizi, Jagannathan Anudiipnath, Zhahir Amzari, Azami Muhammad Hanafi, Abidin Razali, Noordin Mohd Nor Hafizi, Nordin Norzaima   +6 more
doaj   +2 more sources

Rocket Engine Vacuum Nozzle 3D Printing: Manufacturing, Weight, and Cost Savings [PDF]

Engineering Proceedings
Metallic materials additive manufacturing is extremely challenging nowadays, while aircraft manufacturers are trying to adapt the newly developed technology to produce parts of complex geometry with minimum materials losses.
Nikolaos D. Alexopoulos, Vasileios Zeimpekis, Evangelos Vasileiou, Nikolaos Thomaidis, Theodoros Souxes, Ilona Lazaridou, Maksym Lutsyk, Roman Vorobev, Evgeniy Karakash, Elena Karpovich, Olexandr Grydin   +10 more
doaj   +2 more sources

Cattaneo-Christov heat flux and entropy generation on hybrid nanofluid flow in a nozzle of rocket engine with melting heat transfer

Case Studies in Thermal Engineering, 2021
This study aims to scrutinize the mathematical formulations of hybrid nanoliquid filled with thermal radiation, Cattaneo-Christov heat theory and melting phenomenon in a nozzle of rocket engine that includes hybrid nanoparticles (CoFe2O4,CdTe,TiO2,Cu&CuO)
Hassan Waqas, Taseer Muhammad, Sobia Noreen, Umar Farooq, Metib Alghamdi   +4 more
doaj   +2 more sources

Transonic Flow Field Analysis of a Minimum Nozzle Length Rocket Engine [PDF]

INCAS Bulletin
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.
Omar ABADA, Hakim KBAB, Sidali HAIF
doaj   +2 more sources

Results of experimental evaluation of the possibility of using an annular nozzle with a flat central body as part of a stand liquid rocket engine chamber

Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение
One of the ways to increase the efficiency of a rocket engine chamber is to ensure the fixed nozzle operation in the design mode over the entire range of altitudes (ambient pressure) of engine operation.
A. A. Kirshina, A. A. Levikhin, A. Yu. Kirshin   +2 more
doaj   +3 more sources

Analysis of Various Nozzle Designs to Improve Rocket Engine Performance

International Journal of Inventions in Engineering & Science Technology
This paper suggests a nozzle geometry that has the greatest potential to improve rocket engine parameters, such as thrust and efficiency, beyond their current status. Increasing these would increase the payload mass that can be sent into space and help create a viable Single-Stage-to-Orbit (SSTO) platform.
Vidyut C Murali
openaire   +2 more sources

Multi-Objective Optimization of Rocket-Type Pulse Detonation Engine Nozzles

Aerospace
This numerical study addressed the multi-objective optimization of a rocket-type Pulse Detonation Engine nozzle. The Pulse Detonation Engine consisted of a constant length, constant diameter cylindrical section plus a nozzle that could be either ...
Alberto Gonzalez-Viana, Francisco Sastre, Elena Martin, Angel Velazquez   +3 more
doaj   +2 more sources