@techreport{oai:jaxa.repo.nii.ac.jp:00043209,
 author = {宮川, 淳一 and 廣瀬, 直喜 and 河合, 伸坦 and Miyakawa, Jun-ichi and Hirose, Naoki and Kawai, Nobuhiro},
 month = {Nov},
 note = {The progress of computational aerodynamics over the past decade has been so tremendous, partly pushed by the rapid advance in computer hardware, that aircraft designers have obtained an alternative tool for aerodynamic analysis comparable to wind tunnel testing. The Navier-Stokes computation, which has been used successfully in research recently, is also likely to become a practical tool for analyzing viscous flows. NSFOIL, the high Reynolds number transonic airfoil analysis code developed at NAL, has been verified by comparing it with the results of high Reynolds number wind tunnel tests at NAL. This paper presents the NSFOIL computation of the transonic airfoil with aileron. following the clean airfoil result presented at the previous symposium in 1984. To show the effectiveness of this new code, the comparison of numerical results with the experiments is also presented in this paper., 資料番号: NALSP0005029, レポート番号: NAL SP-5},
 title = {遷音速翼型のエルロン効きの風洞試験と計算の対応},
 year = {1985}
}