@techreport{oai:jaxa.repo.nii.ac.jp:00001907,
 author = {足立, 憲彦 and 小林, 宙 and 箱島, 秀昭 and 西沢, 啓 and Adachi, Norihiko and Kobayashi, Hiroshi and Hakojima, Hideaki and Nishizawa, Akira},
 month = {Jul},
 note = {本報告では電動モータで推進系を駆動する電動化航空機における，推進用プロペラブレードを用いたエネルギ回生効果について検討する．風速，直径，ブレードピッチなどをパラメータとして行った風洞試験の結果，小型機においては降下時に回生を行うことで位置エネルギの10％程度を回収できる見通しが得られた．また，熱線流速計を用いたブレードの後流計測から，回生時に発生するプロペラ抗力にはプロペラ半径の60%よりハブ側の翼素における局所抗力の影響が大きいことが分かった．, When an aircraft powered by an electrical motor (electric aircraft) with rechargeable batteries descends, it is easy to utilize wind power for charging the batteries by rotating propeller passively. In this study we examined characteristics of propeller-blades to regenerate energy in some conditions in a wind tunnel by using model-aircraft propellers and main rotor for model-helicopter. The changed conditions are follows; 1) wind speed, 2) blade diameter and 3) blade pitch angle. Based on the results of this experiment, it is found that electric aircraft can regain 10% of potential energy while descending. In addition, slipstream measurements were conducted and local drag and local thrust of blade elements were calculated. These results demonstrated that local drag is mainly generated by blade elements in r/R less than 0.6., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530029000, レポート番号: JAXA-RR-15-001},
 title = {電動化航空機におけるプロペラブレードを用いたエネルギ回生に関する実験的研究},
 year = {2015}
}