Numerical Simulation of Nozzle Flow Field with Secondary Injection Thrust Vector Control

H. R. Noaman; Tang Hai Bin; Elsayed Khalil

doi:10.1051/matecconf/201817901003

Numerical Simulation of Nozzle Flow Field with Secondary Injection Thrust Vector Control

H. R. Noaman^*
, Tang Hai Bin
, Elsayed Khalil

^*Corresponding author for this work

School of Astronautics

Research output: Contribution to journal › Conference article › peer-review

4 Scopus citations

Abstract

Numerical simulations are performed to characterize the secondary injection thrust vector control. For this objective the following measurements were taken: considering the flow to be compressible and turbulent using Realizable k-ϵ turbulence model accompanied by enhanced wall treatment, the comparison between the CFD results and the experimental results shows a very good agreement. Then a parametric study on injection mass flow rate (changing secondary stagnation pressure) with the same injection location and injection angle is done. The results stated that increasing the injectant mass flow rate lead to shock impingement from opposite wall at secondary stagnation pressure 1.4 of the primary stagnation pressure.

Original language	English
Article number	01003
Journal	MATEC Web of Conferences
Volume	179
DOIs	https://doi.org/10.1051/matecconf/201817901003
State	Published - 26 Jul 2018
Event	2018 2nd International Conference on Mechanical, Material and Aerospace Engineering, 2MAE 2018 - Wuhan, China Duration: 10 May 2018 → 13 May 2018

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10.1051/matecconf/201817901003

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title = "Numerical Simulation of Nozzle Flow Field with Secondary Injection Thrust Vector Control",

abstract = "Numerical simulations are performed to characterize the secondary injection thrust vector control. For this objective the following measurements were taken: considering the flow to be compressible and turbulent using Realizable k-ϵ turbulence model accompanied by enhanced wall treatment, the comparison between the CFD results and the experimental results shows a very good agreement. Then a parametric study on injection mass flow rate (changing secondary stagnation pressure) with the same injection location and injection angle is done. The results stated that increasing the injectant mass flow rate lead to shock impingement from opposite wall at secondary stagnation pressure 1.4 of the primary stagnation pressure.",

author = "Noaman, \{H. R.\} and Bin, \{Tang Hai\} and Elsayed Khalil",

note = "Publisher Copyright: {\textcopyright} The Authors, published by EDP Sciences 2018.; 2018 2nd International Conference on Mechanical, Material and Aerospace Engineering, 2MAE 2018 ; Conference date: 10-05-2018 Through 13-05-2018",

year = "2018",

month = jul,

day = "26",

doi = "10.1051/matecconf/201817901003",

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journal = "MATEC Web of Conferences",

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TY - JOUR

T1 - Numerical Simulation of Nozzle Flow Field with Secondary Injection Thrust Vector Control

AU - Noaman, H. R.

AU - Bin, Tang Hai

AU - Khalil, Elsayed

N1 - Publisher Copyright: © The Authors, published by EDP Sciences 2018.

PY - 2018/7/26

Y1 - 2018/7/26

N2 - Numerical simulations are performed to characterize the secondary injection thrust vector control. For this objective the following measurements were taken: considering the flow to be compressible and turbulent using Realizable k-ϵ turbulence model accompanied by enhanced wall treatment, the comparison between the CFD results and the experimental results shows a very good agreement. Then a parametric study on injection mass flow rate (changing secondary stagnation pressure) with the same injection location and injection angle is done. The results stated that increasing the injectant mass flow rate lead to shock impingement from opposite wall at secondary stagnation pressure 1.4 of the primary stagnation pressure.

AB - Numerical simulations are performed to characterize the secondary injection thrust vector control. For this objective the following measurements were taken: considering the flow to be compressible and turbulent using Realizable k-ϵ turbulence model accompanied by enhanced wall treatment, the comparison between the CFD results and the experimental results shows a very good agreement. Then a parametric study on injection mass flow rate (changing secondary stagnation pressure) with the same injection location and injection angle is done. The results stated that increasing the injectant mass flow rate lead to shock impingement from opposite wall at secondary stagnation pressure 1.4 of the primary stagnation pressure.

UR - https://www.scopus.com/pages/publications/85063183090

U2 - 10.1051/matecconf/201817901003

DO - 10.1051/matecconf/201817901003

M3 - 会议文章

AN - SCOPUS:85063183090

SN - 2261-236X

VL - 179

JO - MATEC Web of Conferences

JF - MATEC Web of Conferences

M1 - 01003

T2 - 2018 2nd International Conference on Mechanical, Material and Aerospace Engineering, 2MAE 2018

Y2 - 10 May 2018 through 13 May 2018

ER -

Numerical Simulation of Nozzle Flow Field with Secondary Injection Thrust Vector Control

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