@techreport{oai:jaxa.repo.nii.ac.jp:00043167,
 author = {里深, 信行 and 西田, 雄亮 and Satofuka, Nobuyuki and Nishida, Yuusuke},
 month = {Nov},
 note = {An unconditionally stable explicit method has been applied to compute compressible laminar flows past an NACA0012 airfoil. The method is based on a combination of central differencing for spatial derivatives with a rational Runge-Kutta time integration scheme. Both transonic (M, An unconditionally stable explicit method has been applied to compute compressible laminar flows past an NACA0012 airfoil. The method is based on a combination of central differencing for spatial derivatives with a rational Runge-Kutta time integration scheme. Both transonic (M = 0.8) and supersonic (M = 2.0) flow cases have been calculated for various Reynolds numbers. Physically plausible results are obtained for each case within practically feasible CPU time., 資料番号: NALSP0003025, レポート番号: NAL SP-3},
 title = {無条件安定な陽的差分法による翼型まわりの粘性流の解析},
 year = {1984}
}