@techreport{oai:jaxa.repo.nii.ac.jp:00043203,
 author = {信太, 良文 and 桑原, 邦郎 and Shida, Yoshifumi and Kuwahara, Kunio},
 month = {Nov},
 note = {In this paper, two unsteady flows around an airfoil are studied by numerically solving the two-dimensional compressible Navier-Stokes equations. One is the flow around an NACA0012 airfoil at Mach 0.4 at an angle of attack of 15 degrees. The Reynolds number is 1000000. The other is the dynamic stall problem around an NACA0012 airfoil. The Mach number is 0.3. The Reynolds number is 4000000. The block pentadiagonal matrix scheme, a new method which is based on the approximate factorization scheme, is adopted. In the former case, a strong suction peak is observed near the leading edge in the computational results obtained by using a fine mesh. It apeared to be maintained by turbulence-like small vortices. In the case of the dynamic stall, two noteworthy features are observed in the computation using the fine mesh. The first is that when vortex separation occurs on the upstroke, many small vortices are separated from all parts of the surface, rather them just one large vortex from the leading edge as one might expect. The second is that the flow re-attaches when the angle of attack is about 8 degrees on the down-stroke. The lift stall is clealy captured in this study., 資料番号: NALSP0005023, レポート番号: NAL SP-5},
 title = {大迎角の翼をすぎる遷音速流},
 year = {1985}
}