@article{oai:nagoya.repo.nii.ac.jp:00012002,
 author = {東, 大輔 and AZUMA, Daisuke and 中村, 佳朗 and NAKAMURA, Yoshiaki},
 issue = {626},
 journal = {日本航空宇宙学会論文集},
 month = {Mar},
 note = {The low-speed flow for a 45deg-swept delta wing is numerically simulated to examine the effects of a hybrid method consisting of leading edge rotation and trailing edge jet on aerodynamic forces. Computation has been performed at an angle of attack of 20deg and a Reynolds number of 2.0×104 based on the wing root chord. Under these conditions, the flow is fully separated from the wing surface, so that no suction peaks due to leading edge vortices are observed over the upper surface of the wing. By using the hybrid method, lift coefficient can become 85% higher than that of the baseline delta wing without any high lift device.},
 pages = {116--120},
 title = {前縁回転/後縁ジェットハイブリッド法によるデルタ翼揚力増加},
 volume = {54},
 year = {2006}
}