Aerodynamics Analysis of NASA Common Research Model Using BCM-TAS Coupling Flow Solver

• MAKINO Shinya

  東北大学 流体科学研究所

• MISAKA Takashi

  東北大学 流体科学研究所

• OBAYASHI Shigeru

  東北大学 流体科学研究所

• HIROSE Takuya

  金沢工業大学

• SASAKI Daisuke

  金沢工業大学

Bibliographic Information

Other Title

• BCM-TASカップリングソルバーを用いたNASA CRMの空力解析

Abstract

In this study, the aerodynamic performance of NASA Common Research Model (wing-body configuration) was analyzed by coupling a Cartesian mesh CFD solver of Building-Cube Method (BCM) and an unstructured mesh CFD solver of Tohoku University Aerodynamic Simulation (TAS) codes. The thin boundary layer was handled by the unstructured body-fitted mesh near wall, while the vortical wake was effectively resolved by the multi-level Cartesian mesh of BCM. The computational results were compared with those of the transonic wind tunnel tests for validation. The lift and drag coefficients as well as pressure coefficient around wing sections were comparable with the experimental and numerical results by other participants. In addition, the advantage of the multi-level Cartesian mesh was presented by the sharply captured wake in the present simulation. It is confirmed that results of the BCM-TAS Coupling Flow Solver is generally agreed well with the experimental data in aerodynamic predictions and wake analyses.

Journal

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

  AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 17 (0), 199-208, 2018

  THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Keywords

• CFD
• Cartesian-Unstructured Coupling Solver
• NASA Common Research Model

Details

• CRID: 1390001288043034368
• NII Article ID: 130007403849
• DOI: 10.2322/astj.jsass-d-17-00038
• ISSN: 18840477
• Web Site: https://www.jstage.jst.go.jp/article/astj/17/0/17_JSASS-D-17-00038/_pdf
• Text Lang: ja
• Data Source:
  • JaLC
  • Crossref
  • CiNii Articles
  • KAKEN
• Abstract License Flag: Disallowed