Japan Defense Agency Technical Research and Development Institute
Japan Defense Agency Technical Research and Development Institute
Mitsubishi Heavy Industries Ltd
Kawasaki Heavy Industries Ltd
Fuji Heavy Industries Ltd
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory
巻
44
ページ
363 - 368
発行年
1999-12
会議概要（会議名, 開催地, 会期, 主催者等）
航空宇宙技術研究所 16-18 Jun. 1999 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 16-18 Jun. 1999 Tokyo Japan
This paper shows the results of the CASPER (Computational Aerodynamics System for Performance Evaluation and Research) that has been developed in Technical Research and Development Institute of Japan Defense Agency. The CASPER is a CFD (Computational Fluid Dynamics)-based design system for the aerodynamic design of various advanced aircraft. The present CFD code consists of three-dimensional Euler analysis solver using structured and unstructured grids. In order to verify the code, transonic (free-stream Mach number M(sub infinity) = 0.9) and supersonic (M(sub infinity) = 1.2) flow fields around an F-16A aircraft configuration were computed. The computational results of lift, drag, pitching moment and pressure coefficients are in a good agreement with those of wind-tunnel experiments. It becomes clear that the CASPER is a very powerful tool for aerodynamic design of complete aircraft configurations.
CASPERによるF-16A戦闘機のCFD計算とその検証
nalsp0044058.pdf
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