@inproceedings{oai:jaxa.repo.nii.ac.jp:00006464,
 author = {堀江, 栄之 and 松島, 紀佐 and 中橋, 和博 and Horie, Hideyuki and Matsushima, Kisa and Nakahashi, Kazuhiro},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2004論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2004},
 month = {Mar},
 note = {For computational mechanics, it is necessary to mathematically represent airfoil geometries. The PARSEC method is one of the best methods to mathematically express airfoil geometries with relatively small number of free design parameters. The PARSEC method has been mostly used for transonic airfoils. In this paper, the PARSEC method is examined if it has flexibility in designing airfoils. Also, a new method of the airfoil parameterization based on PARSEC method is proposed. The both methods are compared in terms of the accuracy and flexibility of representing different kinds of airfoil shapes. NACA2212, RAE2822, and the wing section of the main wing of NEXST-1, which is the prototype of a small supersonic airplane being developed by JAXA, are used as an example of subsonic, transonic, and supersonic airfoil, respectively. The results show that the airfoils represented by the PARSEC method have deficiency on the representing capability if an airfoil is highly cambered or it is for supersonic. The proposed method shows better capability to accurately represent large variety of airfoil shapes. In other words, it can extend the design space without the increase of free design parameters., 資料番号: AA0048469024, レポート番号: JAXA-SP-04-012},
 pages = {145--150},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {バーチャルエンジニアリングのための翼型関数表現},
 volume = {JAXA-SP-04-012},
 year = {2005}
}