Earticle

초록

영어

In order to verify the feasibility of the method of numerical simulation of supersonic noise, the flow field and noise at far field of a small solid fuel rocket engine F tested by National Aeronautics and Space Administration's Langley Research Center (NASA) was simulated by computational fluid dynamics (CFD) and computational aeroacoustics (CAA). The conjunction with large eddy simulation and FW-H integral method is adopted to simulate spectrums of the noise. The conjunction with large eddy simulation and Möhring sound analogy is adopted to predict the direction of the noise at the near-field. Comparing the result with the experimental data, the flow field coincides well, and in the sound field, the low and medium-frequency sound pressure level coincides well too, and the high-frequency sound pressure level is slightly lower than the estimated value. The error of overall sound pressure level of the measure point is small. The sound field resulted by high temperature, high pressure and high velocity fluid is simulated successfully.

목차

Abstract
 1. Introduction
 2. Verification Model
 3. Engine Noise Simulation
  3.1. Flow Field Simulation
  3.2. Sound Field Simulation
 4. Simulation Process
  4.1. Computational Domain
  4.2. Boundary Conditions
  4.3. Computational Grid
  4.4. Numerical Simulation
 5. Conclusions
 References

키워드

저자

• Aiqin Li [ Beijing Institute of Petro-chemical Technology, Beijing 102617,China ]
• Jiecheng Yu [ Beijing Institute of Petro-chemical Technology, Beijing 102617,China ]

참고문헌

발행기관

간행물

표지보기 관심저널 등록

• 간행물명

  International Journal of Hybrid Information Technology

• 간기

  격월간

• pISSN

  1738-9968

• 수록기간

  2008~2016

• 십진분류

  KDC 505 DDC 605