Computational Prediction of Acoustic Waves from a Subscale Rocket Motor

• NONOMURA Taku

  Institute of Space and Astronautical Science, JAXA

• MORIZAWA Seiichiro

  Tohoku University

• OBAYASHI Shigeru

  Tohoku University

• FUJII Kozo

  Institute of Space and Astronautical Science, JAXA

抄録

For improvement of prediction of acoustics waves from a rocket plume, validation studies of numerical simulation are performed using experimental data of acoustics waves from subscale rocket motors, and prediction accuracy of numerical simulation is discussed. Experimental data of flow and acoustics fields of a solid motor and a H2-AIR liquid motor are used as the reference. The computational results of the far-field OASPL agree with experimental data within the error of approximately 5dB. The result shows that the current numerical methods well predict Mach waves at downstream side even though the results of far-field PSD are slightly overestimated. Meanwhile, it is difficult to capture shock associated acoustic waves and fine-scale turbulence acoustic waves at upstream side and the results of far-field PSD are underestimated. In addition, difference between single and multicomponent in the computational results is also small.

収録刊行物

• TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12 (ists29), Pe_11-Pe_17, 2014

  一般社団法人 日本航空宇宙学会

キーワード

• Rocket Plume
• Supersonic Jet
• Computational Aeroacoustics
• Multicomponent Compressible Flows

詳細情報

• CRID: 1390282680296970752
• NII論文ID: 130004548632
• DOI: 10.2322/tastj.12.pe_11
• ISSN: 18840485
• Web Site: https://www.jstage.jst.go.jp/article/tastj/12/ists29/12_Pe_11/_pdf
• 本文言語コード: en
• データソース種別:
  • JaLC
  • Crossref
  • CiNii Articles
  • KAKEN
• 抄録ライセンスフラグ: 使用不可