@inproceedings{oai:jaxa.repo.nii.ac.jp:00038273,
 author = {村山, 光宏 and 富樫, 史弥 and 中橋, 和博 and 松島, 紀佐 and 加藤, 琢真 and Murayama, Mitsuhiro and Togashi, Fumiya and Nakahashi, Kazuhiro and Matsushima, Kisa and Kato, Takuma},
 book = {航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2002論文集, Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2002},
 month = {Mar},
 note = {In this paper, numerical simulations of aerodynamic response to changes of the deflection angle of a longitudinal control surface of NAL experimental supersonic airplanes are discussed. To treat the change of the deflection angle of the control surface efficiently, an unstructured dynamic mesh method with surface grid movement is used. Computations of a rocket powered experimental supersonic airplane and a jet powered experimental supersonic airplane are performed at the supersonic cruising Mach numbers (M(sub infinity) = 2.0 and 1.7) and a transonic Mach number (M(sub infinity) = 0.95). The computational results are compared and are discussed., 資料番号: AA0045948052, レポート番号: NAL SP-57},
 pages = {292--297},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {航空機舵角変化に対する空力応答の数値シミュレーション},
 volume = {57},
 year = {2003}
}