@inproceedings{oai:jaxa.repo.nii.ac.jp:00003253,
 author = {清水, 亮介 and 松島, 紀佐 and 五島, 健太郎 and Shimizu, Ryosuke and Matsushima, Kisa and Goshima, Kentaro},
 book = {宇宙航空研究開発機構特別資料: 第49回流体力学講演会/第35回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 49th Fluid Dynamics Conference / the 35th Aerospace Numerical Simulation Symposium},
 month = {Dec},
 note = {第49回流体力学講演会/第35回航空宇宙数値シミュレーション技術シンポジウム (2017年6月28日-30日. 国立オリンピック記念青少年総合センター), 渋谷区, 東京, 49th Fluid Dynamics Conference /the 35th Aerospace Numerical Simulation Symposium (June 28-30, 2017. National Olympics Memorial Youth Center), Shibuya-ku, Tokyo, Japan, This article discusses a wake integration technique for accurate drag prediction applied to results by RANS CFD flow simulation. At first, the concept of wake integration is reviewed and the process of a momentum balance approach to lead a primitive wake integration formula is investigated. The formula is applied to several configurations, including a wing in subsonic flow, a wing in transonic flow and NASA-CRM wing-fuselage in transonic flow. Drag values are obtained by using two techniques, one is the wake integration and the other is the near field method which has been commonly used standard one for CFD drag calculation. At the present, the latter method is thought to be more reliable, so the accuracy of drag coefficient by the wake integration is evaluated by comparing them with the one calculated by the near field method. We have found the accuracy of drag calculated by wake integration is related to various aspects, including an axial position of downstream wake plane, a grid type, a grid density, a flow regime, and boundary locations., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1730011019, レポート番号: JAXA-SP-17-004},
 pages = {127--132},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {航空機の後流積分による抵抗計算の考察},
 volume = {JAXA-SP-17-004},
 year = {2017}
}