Optics and Photonics Journal, 2013, 3, 90-93

doi:10.4236/opj.2013.32B023 Published Online June 2013 (http://www.scirp.org/journal/opj)

Based on Fluent Numerical Calculation of Refractive

Index on Rocket Engine Nozzle Plume

Qiangfeng Huang1, Xiong Wan1,2* Zhi min Zhang1, Huaming Zhang1,

Hengyang Shen1, Tingting Du1

1Key Laboratory of Nondestructive Testing (Ministry of Education), Nanchang, Hangkong University, Nanchang, Jiangxi, China

2Key Laboratory of Spatial Active Opto-electronic Techniques, Shanghai Institute of Technical, Physics,

Chinese Academy of Sciences, Shanghai, China

Email: *nchundt114@126.com

Received 2013

ABSTRACT

Numerical 2D simulation and research on internal flow field and external flow field of rocket motor nozzle using

FLUENT software. Analyze the flow condition of internal flow field and external flow field, and according to add in the

amount of the different gas components, obtain the clear distribution of contour of density flow field, pressure flow

field and various material components and so on. Simulation results agree with the results observed from the test on the

ground, and provide reference for s ol id rocket m ot or development.

Keywords: Rocket Engine Nozzle; Nozzle Plume; Fluent; Numerical Simulation

1. Introduction

The plume of the rocker motor is composed by the high

temperature, high-pressure, high-flow combustion prod-

ucts of propellan t, wh ich g o thoug h Lava l-nozzle f low b y

static state and form a supersonic gas flow on the cross

section of a nozzle. The exhaust plume of rocket motor

nozzle is composed by H2O, CO2, CO, H2 and N2 and so

on. According to design conditions of the difference,

they will make larger difference among flow field calcu-

lation, so in order to obtain the best density field contours,

here we chose the parameters of 7500 N thrust for nu-

merical calculation. In this paper, some propellant was

thermodynamically calculated, and the total temperature

and the total pressure of the gas and the mass fraction of

the ingredients of combustion resultants were obtained.

Meanwhile, the finite-rate chemical reaction model of

flow field of exhaust plume was built. Using fluent cal-

culation software solve the NS equation and the compo-

nent transport equation, so temperature field and density

field and ingredient distribution curves of the exhaust

plume were calculated, then the relationship of making

use of density field and several ingredient contents solve

the distribution of refractive index field which compare

with the experimental results again, it is available to v er-

ify the calculation method.

2. Calculation Conditions and Boundary

Condition

In order to numerical calculation which is convenient,

some rocket motor model is predigested processing. Se-

lecting the co mbustor end which is the nozzle in let is also

the gas inlet. In order to obtain higher calculation accu-

racy, the compressible, Reynolds-averaged difference N-S

equation and second order upwind are adopted to solve

the model when calculating internal flow field and nozzle

plume area. The turbulence model will adopt RNG k-

equation [1] turbulence model, and using non-equilib-

rium wall function [2] near the wall is processing. The

calculation method will adopt PISO algorithm which

must solve the pressure correction equation twice. So it

needs additional storage space to calculate the source

term in the secondary pressure correction equation. Al-

though this me t h o d invo lves more ca lc ulati ons, compar ed

to other algorithms, its speed fast, iteration converges

faster, and efficiency is very high.

2.1. Computational Domain and Boundary

Conditions

Computational domain of nozzle and flow field of plume

is shown in Figure 1. Effective length of the plume do-

main is about 10 m × 3 m. The ABHI area is the ter-

minal area of combustion chamber which is also nozzle

area, the EFGH area and the CDEHB area are plume

*Corresponding author.

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