Numerical Investigation of the Perfomance of Convergent Divergent Nozzle (original) (raw)
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5th International Conference on Engineering, Research, Innovation and Education (ICERIE), 2019At: Shahjalal University of Science & Technology (SUST), Sylhet, bangladesh, 2019
A rocket engine nozzle is the main component of the rocket propulsion system. To produce thrust Ramjets, Scramjets and rockets all use nozzles to accelerate hot exhaust. Primary design difficulties arise with the nozzle used in a rocket with a wide Mach number capability. This work centers on the modeling of a convergent-divergent nozzle for compressible flow using computational fluid dynamics (CFD). CFD, a vital branch of fluid dynamics to solve and analysis different fluid flows by using numerical methods and algorithms. Boundary conditions are required to measure the interaction of the fluid with the surfaces. A bell nozzle contour has developed in MATLAB and analyzed it for different thermodynamic parameters. Density and temperature variations often perform a significant role in compressible flow. Hence, by varying the nozzle length this study provides additional information on Mach number behavior, shock location, and pressure distribution. The simulation was performed in ANSYS and both the k-turbulence modeling method was used to compare the results.
IRJET- CFD ANALYSIS OF CONVERGENT AND DIVERGENT NOZZLE
IRJET, 2020
A nozzle is a very essential device that is used to control character of the fluid. The main purpose of the nozzle is to increase the velocity in one way or another. De Laval nozzle is a converging-diverging nozzle which has the ability to convert the chemical energy (high pressure) into kinetic energy (high velocity and low pressure). De-Laval nozzle has mainly 3 parts such as throat, diverging part, and converging part. Expansion in C-D nozzle has been studied and analyzed by experimentation moreover as numerically by numerous researchers with an objective to optimize the performance beneath given conditions. Within the gift work, supersonic flow through the rocket nozzle has been simulated mistreatment numerical methodology. The analysis has been performed keeping the same input and according to the shape of the nozzle. Our objective is to investigate the best suit nozzle which gives high exit velocity among the different cross-sections considered. The main aim of this paper is to a proper comparison with theoretical data to determine the behavior of fluid during the movement of fluid inside the nozzle. Therefore CFD analysis is being done using ANSYS 16. The paper contains a proper analysis of the convergent-divergent nozzle. Analysis of Mach number and velocity is done inside the nozzle
Modeling and simulation of Convergent-Divergent Nozzle Using Computational Fluid Dynamics
CFD is a branch of Fluid Mechanics which rely on numerical methods and algorithms to solve and analyze problem that involves fluid flow. CFD analysis has been conducted to analyze flow pattern of supersonic rocket nozzle at various degree of divergent angle, mach numbers etc. This paper aims to study the behavior of flow in convergent divergent nozzle by analyzing various parameters like pressure, temperature and velocity using computational fluid dynamics software(C.F.D).These results were further plotted comparing them with analytical values.
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In this paper numerical analysis of compressible fluid in a convergent- divergent nozzle in supersonic- subsonic flow, semi-one dimensional conditions and long with the shock has been investigated. Shock occurrence point is considered in X/L=3/4, and its results are compared with analytical amounts. Governing equations written in conservation form and artificial non-viscosity term is used to prevent high vibrations in shock area in momentum equation. Because of changing cross section along the flow, all fluid characteristics would be considered a function of x. so by choosing an appropriate control volume, the main equations include continuity, momentum and energy were discrete .To solve the main equations, McCormack explicit method are used.
IRJET- CFD Analysis of Convergent Divergent of Supersonic Nozzle
IRJET, 2020
Expansion in C-D nozzle has been studied and analyzed by experimentation moreover as numerically by numerous researchers with an objective to optimize the performance beneath given conditions within the gift work supersonic flow through the rocket nozzle has been simulated mistreatment numerical methodology. The parameters like physicist number, static pressure and shocks square measure discovered for cone-shaped and contour nozzles using axisymmetric model in ANSYS FLUENT 16® computer code. The occurrences of shocks for the cone-shaped nozzles were discovered alongside the opposite parameters for various divergent angles. The parameters beneath observation square measure compared there upon of contour nozzle for individual divergent angles by maintaining the water, outlet and throat diameter and lengths of oblique and divergent parts as same. The convergent portion and throat diameter square measure unbroken constant across the cases. The phenomenon of shock was pictured and also the results showed shut similitude in formation of physicist disk and its reflection patterns as reportable in numerous experimental studies on growth in cone-shaped C-D nozzles with lower divergent angles. No occurrence of shocks is discovered with higher divergent angles. Results delineated higher exit speed and better degree of flow separation with contour nozzles compared to it with corresponding cone-shaped nozzles.
Applying Numerical Simulation to Analyse the Performance of Nozzles
—CFX is applied to study of the transonic multicomponent gas field in the adjustable convergent-divergent nozzles of the aero engine. The influences of different flight conditions on the three-dimensional transonic flow fields are analyzed numerically. The accuracy of the k-omega turbulence model is verified through the comparison between the numerical results and experiment data. And this turbulence model is used to predict transonic flows in general convergent-divergent nozzles. Calculations demonstrate that the average Ma number increases and average temperatures decrease gradually at the outlet of nozzle with the increase of flight altitude. It can be found that variation trend of the flow parameters is reasonable in the researched objects. Numerical simulation is a useful method to consider the effect of wall temperature distributions and to analyze the influence of the exhaust temperature on the infrared radiation. Numerical simulation is appropriate for the improvement and the design of aero engine.
Shock waves formation from a converging-diverging nozzle
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The project is about studying the whole rocket. We will work on comparing between analytical and theory results on the converging diverging (C-D) nozzle, also called de Laval nozzle for an isentropic flow, a normal shock wave in the diverging section, an oblique shock wave and an expansion at the exit. Then we will simulate the flow at the upper surface of the rocket by CFD, considering the upper area as diamond shaped. The aim of the simulation is to show the oblique shock wave created by supersonic speed and doesn’t intersect with the rest of the rocket, reducing overall the drag.
IRJET- Modelling and Analysis of a Convergent -Divergent Nozzle
IRJET, 2021
Nozzle is a part of the propulsion system which is used to accelerate the hot gases flowing through it. The nozzle geometry is highly important because it directly affect the overall performance of propulsion system. Also, design of nozzle is an important aspect for achieving the maximum Mach number or supersonic speed. To achieve supersonic speed a type of nozzle called Convergent-Divergent nozzle or otherwise known as the de Laval nozzle or CD nozzle is used which converts the high temperature, high pressure, and low velocity gas into high velocity and low pressure gas at the exit. The main aim of this work is to model Convergent-Divergent nozzle and analyse the variation in flow parameters that are static pressure, velocity, static temperature and Mach number by modifying the nozzle divergent angle, keeping same throat and inlet diameter and by using the optimum convergent angle of 28.5°. Analysis is carried out for divergent angles 5°, 10°, 15° and 20° using computational fluid dynamics software(CFD). CFD results were compared with the theoretical results. Variation in flow parameters at the nozzle outlet is studied so as to find the optimum divergent angle for the optimum convergent angle. By considering the results of all the divergent angles 20° gave maximum Mach number that will lead to improve performance of the nozzle and thereby the power and efficiency of a propulsion system.