ファイルインデックス名 : File Index Name : 1155 .A 翼型整理番号      : Airfoil Serial No. : N04-0060-1 翼型名         : Airfoil Name : N.A.C.A. 65-006 翼型ファイル番号    : Airfoil File No. : 1155 翼型情報        : Airfoil Information : Original 算出前縁半径      : Computed L.E.R. : ? 算出前縁傾斜      : Computed Slope of L.E. : ? 算出プログラム番号   : Computed Program No. : B84-902CX6A 座標          : Plot Ordinates : X Y 1.00000 0.00000 0.94801 0.00206 0.89900 0.00517 0.85274 0.00845 0.80903 0.01166 0.76769 0.01468 0.72855 0.01743 0.69146 0.01990 0.65627 0.02209 0.62287 0.02399 0.59112 0.02562 0.56094 0.02697 0.53220 0.02806 0.50483 0.02888 0.47874 0.02944 0.45384 0.02979 0.43007 0.02997 0.40737 0.03000 0.38566 0.02991 0.36489 0.02972 0.34501 0.02944 0.32596 0.02911 0.30771 0.02871 0.29020 0.02826 0.27340 0.02777 0.25728 0.02723 0.24178 0.02666 0.22689 0.02606 0.21257 0.02542 0.19879 0.02476 0.18552 0.02407 0.17275 0.02336 0.16044 0.02263 0.14858 0.02188 0.13713 0.02111 0.12610 0.02032 0.11544 0.01951 0.10515 0.01868 0.09521 0.01782 0.08561 0.01693 0.07633 0.01602 0.06735 0.01509 0.05866 0.01413 0.05026 0.01313 0.04212 0.01209 0.03424 0.01100 0.02660 0.00982 0.01920 0.00857 0.01203 0.00705 0.00508 0.00480 0.00168 0.00282 0.00000 0.00000 0.00000 0.00000 0.00168 -0.00282 0.00508 -0.00480 0.01203 -0.00705 0.01920 -0.00857 0.02660 -0.00982 0.03424 -0.01100 0.04212 -0.01209 0.05026 -0.01313 0.05866 -0.01413 0.06735 -0.01509 0.07633 -0.01602 0.08561 -0.01693 0.09521 -0.01782 0.10515 -0.01868 0.11544 -0.01951 0.12610 -0.02032 0.13713 -0.02111 0.14858 -0.02188 0.16044 -0.02263 0.17275 -0.02336 0.18552 -0.02407 0.19879 -0.02476 0.21257 -0.02542 0.22689 -0.02606 0.24178 -0.02666 0.25728 -0.02723 0.27340 -0.02777 0.29020 -0.02826 0.30771 -0.02871 0.32596 -0.02911 0.34501 -0.02944 0.36489 -0.02972 0.38566 -0.02991 0.40737 -0.03000 0.43007 -0.02997 0.45384 -0.02979 0.47874 -0.02944 0.50483 -0.02888 0.53220 -0.02806 0.56094 -0.02697 0.59112 -0.02562 0.62287 -0.02399 0.65627 -0.02209 0.69146 -0.01990 0.72855 -0.01743 0.76769 -0.01468 0.80903 -0.01166 0.85274 -0.00845 0.89900 -0.00517 0.94801 -0.00206 1.00000 0.00000