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Numerical simulation and verification of rocket engine nozzle flow field based on LS-DYNA |
Received:September 16, 2023 Revised:December 25, 2023 |
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DOI:10.7511/jslx20230916006 |
KeyWord:rocket engines nozzle flow field numerical simulation verification LS-DYNA CE/SE method |
Author | Institution |
王亿明 |
大连理工大学 电气工程学院, 大连 |
周柯江 |
大连理工大学 电气工程学院, 大连 |
张东东 |
大连理工大学 电气工程学院, 大连 ;大连理工大学 分离动力学与控制工程技术中心, 大连 |
范书立 |
大连理工大学 分离动力学与控制工程技术中心, 大连 |
李京杰 |
大连理工大学 分离动力学与控制工程技术中心, 大连 |
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Abstract: |
n order to investigate the flow field characteristics and velocity variation trend of rocket engine nozzles,the CE/SE solver in LS-DYNA software was used to verify the relevant parameters of supersonic axisymmetric nozzles(shrinking-expanding nozzles) from the NPARC verification and validation example library.In this paper,the test medium is air.Under the condition of perfect expansion at Mach number 2.22,the center line velocity of the nozzle and the cross-section velocity at each point on the center line are numerically determined,and the simulation results are compared with the test results.The results show that LS-DYNA software can accurately predict the flow distribution and key parameters in the nozzle,and the calculated results and the velocity variation trend are highly consistent with the experimental data,and the difference between them and the experimental data is less than 10%,which effectively verifies the feasibility of the LS-DYNA software to calculate the flow field of the rocket engine nozzle and the method can be further explored and optimized in future studies |
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