@techreport{oai:jaxa.repo.nii.ac.jp:00002124,
 author = {Lei, Zhong and Lei, Zhong},
 month = {Feb},
 note = {本研究では、低速と高迎角における超音速機形態のまわりの流れ場に関してCFD(Computational Fluid Dynamics)解析を行い、風洞試験と比較し、CFD解析精度を検証した。数種類の高揚力形態の解析により、流れの詳細を調査し、翼前・後縁高揚力装置の有効性を考察した。前縁フラップが、剥離を抑制しボルテックス・フラップとして機能することによって、抵抗を低減する効果を確認した。また、後縁フラップが、キャンバー効果により揚力を増加させ、揚抗比を向上させる効果を確認した。前後縁フラップを組み合わせた複合効果のメカニズムを考察し、前縁付近の吹き上げと後縁付近の吹き下ろしが増加することによって機体の空力性能がさらに改善されることが分かった。最後に、高揚力装置設計について展望を述べる。, Flow field around a configuration of supersonic transport with high-lift devices at low speed and high angle of attack was investigated by solving Reynolds-averaged Navier-Stokes equations. The configuration was consisted of a fuselage and a cranked arrow wing, with leading-edge and trailing-edge flaps. Numerical simulations were conducted and validated at conditions of the wind-tunnel test. Details of flow field at the design condition were analyzed using computational results. Effect of the high-lift devices on aerodynamic performance was discussed. The leading-edge vortices were reduced both in size and in strength by deflecting the leading-edge flap and the drag was reduced. A typical leading-edge vortex flap was confirmed. The trailing-edge flap increased the effective camber of the wing and improved the lift force. Furthermore, it was shown that the aerodynamic performance was improved by combination of the leading-edge and trailing-edge flaps., 資料番号: AA0063943000, レポート番号: JAXA-RR-07-050},
 title = {超音速機高揚力装置に関する数値解析及び考察},
 year = {2008}
}