@techreport{oai:jaxa.repo.nii.ac.jp:00043260,
 author = {越岡, 康弘 and 加茂, 圭介 and 天野, 完一 and Koshioka, Yasuhiro and Kamo, Keisuke and Amano, Kan-ichi},
 month = {Nov},
 note = {Flow field simulations over transonic transport aircraft empennage were carried out based on three-dimensional Navier-Stokes equations. The computations were done for the flow fields of various Mach numbers and angles of attack to investigate the variation of the lift curve slope with Mach number at low angle of attack, and the variation of the lift coefficient with angle of attack at low Mach number. The values of lift curve slope obtained by the computations show good agreement with those by experiments. While the difference between computations and experiments looks a little large about lift coefficient versus angle of attack., 資料番号: NALSP0008007, レポート番号: NAL SP-8},
 title = {ナビェ・ストークス方程式による尾翼回りの流れの解析},
 year = {1987}
}