@article{oai:jaxa.repo.nii.ac.jp:00022620,
 author = {徳川, 直子 and 石川, 敬掲 and 上田, 良稲 and Tokugawa, Naoko and Ishikawa, Hiroaki and Ueda, Yoshine},
 journal = {航空宇宙技術},
 month = {Aug},
 note = {The transition characteristics on candidate shapes were examined numerically and experimentally in order to design a natural laminar flow fuselage nose for supersonic transport. The candidate shapes were designed through axisymmetric sinusoidal deformations added on base shapes. Not only parameters of geometry which define the deformation, but also the conditions of uniform flow were varied to obtain the greatest effect of natural laminar flow. From the results, the natural laminar flow effect was found to be obtained in cases of the small ratio of pressure gradients in azimuthal and axial directions in the side area. The natural laminar flow effect was validated experimentally., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: PA1520035000},
 pages = {55--59},
 title = {正弦波変形による軸対称物体の超音速自然層流効果},
 volume = {13},
 year = {2014}
}