Results 171 to 180 of about 35,059 (238)
Some of the next articles are maybe not open access.
Advanced Computational Flow Analysis - Rocket Engine Nozzle
Asian Journal of Research in Social Sciences and Humanities, 2016Analysed 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.
Sandeep Kumar, M. Arularasu
openaire +3 more sources
Performance prediction and optimization for liquid rocket engine nozzle [PDF]
Aerospace Science and Technology, 2007 An optimization approach, based on computational fluid dynamics methodology, is investigated for the performance prediction and optimization of liquid rocket engine nozzle. The CFD code employs implicit Lower-Upper decomposition (LU) scheme for solving the two-dimensional axisymmetric Navier–Stokes (NS) equations and species transport equations in an ...
Jie Fang +3 more
openaire +2 more sources
Influence of rocket design parameters on engine nozzle efficiencies [PDF]
30th Joint Propulsion Conference and Exhibit, 1994 Using a modified version of JANNAFs Two-Dimensional Kinetic Program (TDK), parametric calculations of rocket nozzles were performed. Efficiencies of energy release in rocket engines are defined. The domain of nozzle losses is classified by two-dimensionality, frictionand kinetic.
Hagemann, G., Manski, D.
openaire +4 more sources
Nanotechnology, 2023
In this research, we utilized artificial neural networks along with the Levenberg–Marquardt algorithm (ANN-LMA) to interpret numerical computations related to the efficiency of heat transfer in a regenerative cooling channel of a rocket engine. We used a
Noor Muhammad, Naveed Ahmed
semanticscholar +1 more source
In this research, we utilized artificial neural networks along with the Levenberg–Marquardt algorithm (ANN-LMA) to interpret numerical computations related to the efficiency of heat transfer in a regenerative cooling channel of a rocket engine. We used a
Noor Muhammad, Naveed Ahmed
semanticscholar +1 more source
Efficiency of rocket engine thrust vector control by solid obstacle on the nozzle wall
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2022The thrust vector control of a rocket engine by disturbing the supersonic flow in its nozzle is used for missile development for various purposes in different countries. Disturbance of the supersonic flow in the jet engine nozzle can be caused by various
G.A. Strelnikov +3 more
semanticscholar +1 more source
Electrification of nozzle in a liquid rocket engine
Combustion, Explosion, and Shock Waves, 1995A method of electrical-physical diagnostics is developed and experimental studies are conducted of the process of nozzle electrification in a liquid rocket engine operating on a hydrocarbon fuel. The highest electric potential is shown to be realized at about a stoichiometric ratio of the components, i.e., when the flow velocity, temperature, and ...
A. V. Voronetskii +2 more
openaire +2 more sources
Heat Transfer, 2021
In the present work, a convergent–divergent nozzle with a multi‐inlet combustion chamber of a rocket engine is numerically investigated to precisely understand the flow dynamics and variation of flow properties like pressure, temperature, and velocity ...
Arun Bhaskar, M. Sahu
semanticscholar +1 more source
In the present work, a convergent–divergent nozzle with a multi‐inlet combustion chamber of a rocket engine is numerically investigated to precisely understand the flow dynamics and variation of flow properties like pressure, temperature, and velocity ...
Arun Bhaskar, M. Sahu
semanticscholar +1 more source
Numerical Analysis of Nozzle Material Thermochemical Erosion in Hybrid Rocket Engines [PDF]
Journal of Propulsion and Power, 2012 Ablative materials are commonly used to protect the nozzle metallic housing and to provide the internal contour to expand the exhaust gases in both solid and hybrid rockets. Because of interaction with hot gas, these materials are chemically eroded during rocket firing, with a resulting nominal performance reduction.
BIANCHI, DANIELE, NASUTI, Francesco
openaire +3 more sources
Inviscid Nozzle for Aerospike Rocket Engine Application
Applied Mechanics and Materials, 2015A computational method for the steady 2-D flow in axially symmetrical rocket nozzles with a given profile is developed, in order to determine the Maximum thrust contour of rocket engine nozzles with large expansion ratio. The optimized nozzles proved a more than 10% increase in the integral specific impulse recorded during the variable ...
Florin Radu Bacaran +4 more
openaire +2 more sources
Performance of the aerobell extendible nozzle rocket engine
7th Aerospace Sciences Meeting, 1969Aerobell extendible nozzle rocket engine design and performance, cold flow and simulated hot flow test ...
R. R. Stromsta, G. A. Hosack
openaire +2 more sources