@techreport{oai:jaxa.repo.nii.ac.jp:00043168,
 author = {小野, 清秋 and Ono, Kiyoaki},
 month = {Nov},
 note = {The results of numerical computations on the dynamic stall process of a two dimensional NACA0012 airfoil oscillating in pitch between 0 degree and 20 degrees incidence angles are summarized in this paper. The uniform flow Mach number is set to 0.3. The Beam-Warming finite difference algorithm is applied to solve the time-averaged compressible Navier-Stokes, the laminar compressible Navier-Stokes and the Euler equations. The grid system is constructed based on a body-fitted curvilinear coordinate system for efficient unsteady flow computations. The computational results are compared with the experimental data. The process of the formation of the leading edge separation bubble, its convection along the airfoil surface and its shedding into the wake is fairly well simulated. But the abrupt drop of the lift coefficient is not detected in the computations. Judging from the pressure coefficient distribution, the Euler equations results give the best agreement with the experiment. It suggests that the effective local Reynolds number in the turbulent ealculation is smaller than that in the actual flow field. A more precise estimation of the turbulence viscosity, the artificial one and the truncation error is necessary., 資料番号: NALSP0003026, レポート番号: NAL SP-3},
 title = {大迎角をとる二次元翼まわりの流れの数値解析},
 year = {1984}
}