@inproceedings{oai:jaxa.repo.nii.ac.jp:00003397,
 author = {中道, 二郎 and Nakamichi, Jiro},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of the First International Symposium on Flutter and its Application},
 month = {Mar},
 note = {First International Symposium on Flutter and its Application (May 15-17, 2016. Mielparque-tokyo), Minato-ku, Tokyo, Japan, The Lifting Line Theory is based upon the fact that the local lift at a wing section depends not only on the local section angle of attack but also on the downwash induced by the tailing vortexes shed from the next segments of the wing. It predicts quantitatively the spanwise lift distributions of 3D wing, the induced drag and the load distribution of minimum- drag 3D wing. It is also well consistent with the momentum theory about 3D wing. There are two puzzles for the engineers in the aeronautics, especially for aeroelasticians and aerodynamicians in the world. (i) the collocation point for the numerical solution of lifting surface theory (DLM or VLM) must be at the 3-quarter-chord point of each element. Why? (ii) in the momentum theory about 3D wing, what should be the reference mass to exactly explain the lift and drag? In the present note, the two points are clarified with the help of some mathematical manipulations, using the models of an isolated horseshoe vortex and an elliptically load distributed bound vortex with a trailing vortex sheet., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630046004, レポート番号: JAXA-SP-16-008E},
 pages = {55--58},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {Some confirmations related with prandtl's lifting line theory},
 volume = {JAXA-SP-16-008E},
 year = {2017}
}