@inproceedings{oai:jaxa.repo.nii.ac.jp:00002939,
 author = {青野, 光 and 安養寺, 正之 and 濱田, 大生 and Aono, Hikaru and Anyoji, Masayuki and Hamada, Daiki},
 book = {宇宙航空研究開発機構特別資料: 第50回流体力学講演会/第36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 50th Fluid Dynamics Conference / the 36th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム (2018年7月4日-6日. 宮崎市民プラザ), 宮崎市, 宮崎, 50th Fluid Dynamics Conference /the 36th Aerospace Numerical Simulation Symposium (July 4-6, 2018. Miyazaki Citizen's Plaza), Miyazaki, Japan, The current study reports on the results of two-dimensional Navier-Stokes simulations of an NACA0006 airfoil and force measurements interacting with either an airfoil-wake or a cylinder-wake under the low Reynolds number condition. The configuration of the airfoil-wake is constructed based on a design of Mars airplane unit No.2. The diameter of the cylinder in the configuration of the cylinder-wake is determined by a thickness of the main airfoil of the Mars airplane. The chord-based Reynolds number is 14,000. The angle of attack varies -4 degrees to 10 degrees. The computed aerodynamic coefficients in the airfoil-wake and without the wake interaction cases are in reasonable agreement with the experimental data when the angle of attack is less than 6 degrees. The results show that the lift coefficient and lift curve slope of the NACA0006 reduce due to the wake interaction. The characteristics of the wake depend on the relative configuration and the size and shape of the main object and play an important role in resultant aerodynamics of the horizontal stabilizer of the Mars airplane., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1830029010, レポート番号: JAXA-SP-18-005},
 pages = {117--120},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {低レイノルズ数流れ中の翼の空力特性への後流干渉の影響に関する研究},
 volume = {JAXA-SP-18-005},
 year = {2019}
}