Prediction of Aircraft Dynamic Stability Derivatives Using Time-Spectral Computational Fluid Dynamics

• MIYAJI Koji

  Faculty of Engineering, Yokohama National University

• YOSHIDA Yu

  College of Engineering Science, Yokohama National University

抄録

In this study, the dynamic stability derivatives of an aircraft model are calculated using CFD for the forced-pitch oscillation. The time-spectral, or reduced-frequency, method has been developed for RANS simulations on unstructured grids. It achieves faster computations than the time-marching method for periodically unsteady flows. The efficiency and accuracy of the method are first validated through comparisons with the transonic experiment of a pitching LANN wing. Next, the longitudinal dynamic-stability derivatives of a simplified aircraft model are calculated. Dependency of the damping-in-pitch and oscillatory longitudinal stability on the Mach number agreed reasonably well with the experimental results. Both the instantaneous flow field and frequency characteristics obtained directly from the time-spectral results are discussed to determine the effect of Mach number on the stability derivatives.

収録刊行物

• TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 62 (6), 291-298, 2019

  一般社団法人 日本航空宇宙学会

キーワード

• CFD
• Unstructured Grids
• Aircraft Dynamic Stability

詳細情報

• CRID: 1390564227334936320
• NII論文ID: 130007741729
• DOI: 10.2322/tjsass.62.291
• ISSN: 21894205
• ISSN: 05493811
• Web Site: https://www.jstage.jst.go.jp/article/tjsass/62/6/62_T-18-46/_pdf
• 本文言語コード: en
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