XFOIL Version 6.96 Calculated polar for: GOE 435 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.7275 0.09459 0.09071 -0.0689 0.9293 0.0622 -17.500 -0.7233 0.09240 0.08842 -0.0691 0.9022 0.0623 -17.250 -0.7190 0.09013 0.08600 -0.0696 0.8728 0.0624 -17.000 -0.7152 0.08757 0.08329 -0.0705 0.8477 0.0625 -16.750 -0.7104 0.08500 0.08060 -0.0716 0.8282 0.0626 -16.500 -0.7054 0.08244 0.07794 -0.0728 0.8130 0.0627 -16.250 -0.7024 0.07958 0.07498 -0.0742 0.8003 0.0628 -16.000 -0.6975 0.07699 0.07231 -0.0754 0.7902 0.0628 -15.750 -0.6946 0.07416 0.06941 -0.0767 0.7812 0.0630 -15.500 -0.6952 0.07100 0.06615 -0.0782 0.7720 0.0632 -15.250 -0.6966 0.06775 0.06284 -0.0798 0.7662 0.0635 -15.000 -0.6990 0.06432 0.05935 -0.0814 0.7615 0.0637 -14.750 -0.7020 0.06090 0.05586 -0.0831 0.7565 0.0639 -14.500 -0.7036 0.05769 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0.5402 0.1599 -4.750 0.0523 0.01183 0.00535 -0.1265 0.5345 0.1611 -4.500 0.0823 0.01178 0.00528 -0.1269 0.5288 0.1621 -4.250 0.1119 0.01176 0.00522 -0.1272 0.5228 0.1630 -4.000 0.1415 0.01175 0.00517 -0.1275 0.5168 0.1638 -3.750 0.1722 0.01168 0.00510 -0.1279 0.5138 0.1646 -3.500 0.2025 0.01162 0.00504 -0.1283 0.5104 0.1653 -3.250 0.2326 0.01159 0.00499 -0.1287 0.5066 0.1661 -3.000 0.2624 0.01159 0.00495 -0.1290 0.5023 0.1670 -2.750 0.2917 0.01161 0.00493 -0.1292 0.4971 0.1676 -2.500 0.3219 0.01159 0.00490 -0.1296 0.4941 0.1682 -2.250 0.3525 0.01155 0.00487 -0.1300 0.4923 0.1687 -2.000 0.3831 0.01152 0.00484 -0.1304 0.4902 0.1691 -1.750 0.4134 0.01149 0.00482 -0.1308 0.4876 0.1693 -1.500 0.4435 0.01138 0.00469 -0.1312 0.4847 0.1704 -1.250 0.4734 0.01132 0.00460 -0.1316 0.4817 0.1717 -1.000 0.5030 0.01128 0.00455 -0.1320 0.4785 0.1734 -0.750 0.5322 0.01130 0.00454 -0.1322 0.4746 0.1750 -0.500 0.5622 0.01128 0.00453 -0.1326 0.4721 0.1761 -0.250 0.5928 0.01122 0.00449 -0.1330 0.4703 0.1773 0.000 0.6232 0.01118 0.00447 -0.1334 0.4681 0.1786 0.250 0.6534 0.01115 0.00446 -0.1338 0.4656 0.1797 0.500 0.6832 0.01115 0.00446 -0.1341 0.4627 0.1807 0.750 0.7125 0.01118 0.00446 -0.1343 0.4592 0.1816 1.000 0.7411 0.01124 0.00449 -0.1344 0.4553 0.1824 1.250 0.7694 0.01133 0.00456 -0.1345 0.4511 0.1832 1.500 0.7996 0.01130 0.00455 -0.1348 0.4493 0.1844 1.750 0.8297 0.01125 0.00454 -0.1352 0.4465 0.1875 2.000 0.8593 0.01123 0.00455 -0.1355 0.4427 0.1913 2.250 0.8879 0.01125 0.00457 -0.1356 0.4385 0.1952 2.500 0.9155 0.01132 0.00463 -0.1356 0.4338 0.2014 2.750 0.9446 0.01117 0.00463 -0.1361 0.4297 0.2424 3.000 0.9753 0.01088 0.00468 -0.1369 0.4256 0.3479 3.250 1.0033 0.01097 0.00480 -0.1369 0.4199 0.3621 3.500 1.0291 0.01113 0.00494 -0.1366 0.4131 0.3701 3.750 1.0569 0.01123 0.00507 -0.1365 0.4074 0.3771 4.000 1.0826 0.01140 0.00521 -0.1362 0.3988 0.3816 4.250 1.1069 0.01163 0.00538 -0.1356 0.3888 0.3842 4.500 1.1280 0.01189 0.00559 -0.1345 0.3750 0.3898 4.750 1.1444 0.01222 0.00586 -0.1326 0.3601 0.3937 5.000 1.1615 0.01261 0.00619 -0.1309 0.3463 0.3968 5.250 1.1806 0.01305 0.00657 -0.1296 0.3346 0.3996 5.500 1.1982 0.01357 0.00703 -0.1282 0.3239 0.4020 5.750 1.2188 0.01398 0.00741 -0.1272 0.3162 0.4040 6.000 1.2357 0.01455 0.00793 -0.1258 0.3080 0.4055 6.250 1.2572 0.01493 0.00830 -0.1251 0.3030 0.4076 6.500 1.2766 0.01540 0.00878 -0.1242 0.2976 0.4116 6.750 1.2937 0.01601 0.00936 -0.1230 0.2916 0.4151 7.000 1.3138 0.01648 0.00986 -0.1222 0.2875 0.4185 7.250 1.3337 0.01698 0.01037 -0.1214 0.2834 0.4221 7.500 1.3512 0.01763 0.01101 -0.1204 0.2791 0.4250 7.750 1.3664 0.01841 0.01178 -0.1192 0.2743 0.4271 8.000 1.3853 0.01903 0.01241 -0.1185 0.2713 0.4288 8.250 1.4050 0.01961 0.01301 -0.1179 0.2687 0.4301 8.500 1.4236 0.02027 0.01369 -0.1172 0.2656 0.4339 8.750 1.4395 0.02111 0.01455 -0.1164 0.2623 0.4381 9.000 1.4538 0.02208 0.01553 -0.1154 0.2585 0.4418 9.250 1.4682 0.02307 0.01655 -0.1145 0.2553 0.4453 9.500 1.4876 0.02375 0.01726 -0.1141 0.2533 0.4490 9.750 1.5040 0.02463 0.01818 -0.1134 0.2508 0.4526 10.000 1.5189 0.02562 0.01918 -0.1127 0.2479 0.4554 10.250 1.5312 0.02682 0.02041 -0.1118 0.2445 0.4622 10.500 1.5405 0.02825 0.02186 -0.1108 0.2406 0.4692 10.750 1.5563 0.02922 0.02289 -0.1102 0.2384 0.4770 11.000 1.5712 0.03029 0.02401 -0.1096 0.2363 0.4869 11.250 1.5857 0.03138 0.02518 -0.1090 0.2339 0.5020 11.500 1.5975 0.03271 0.02658 -0.1084 0.2312 0.5238 11.750 1.6069 0.03426 0.02822 -0.1076 0.2284 0.5562 12.000 1.6147 0.03593 0.02997 -0.1068 0.2252 0.5933 12.250 1.6271 0.03727 0.03146 -0.1063 0.2234 0.6337 12.750 1.6534 0.03980 0.03420 -0.1052 0.2194 0.6965 13.000 1.6611 0.04157 0.03604 -0.1045 0.2171 0.7191 13.250 1.6683 0.04336 0.03788 -0.1037 0.2146 0.7376 13.500 1.6716 0.04554 0.04011 -0.1028 0.2118 0.7516 13.750 1.6782 0.04745 0.04206 -0.1021 0.2096 0.7647 14.000 1.6906 0.04883 0.04352 -0.1016 0.2080 0.7783 14.250 1.6984 0.05069 0.04545 -0.1011 0.2061 0.7902 14.750 1.7105 0.05471 0.04958 -0.0999 0.2016 0.8169 15.000 1.7119 0.05722 0.05216 -0.0993 0.1990 0.8351 15.250 1.7093 0.05952 0.05472 -0.0979 0.1965 0.9747 15.500 1.7187 0.06133 0.05657 -0.0977 0.1952 1.0000 15.750 1.7274 0.06317 0.05844 -0.0974 0.1934 1.0000 16.000 1.7314 0.06552 0.06083 -0.0970 0.1915 1.0000 16.250 1.7356 0.06784 0.06318 -0.0966 0.1895 1.0000 16.500 1.7362 0.07056 0.06592 -0.0963 0.1874 1.0000 16.750 1.7351 0.07350 0.06887 -0.0960 0.1851 1.0000 17.000 1.7390 0.07585 0.07125 -0.0957 0.1832 1.0000 17.250 1.7440 0.07815 0.07361 -0.0956 0.1817 1.0000 17.500 1.7497 0.08034 0.07583 -0.0954 0.1799 1.0000 17.750 1.7543 0.08264 0.07816 -0.0953 0.1779 1.0000 18.000 1.7527 0.08568 0.08123 -0.0952 0.1757 1.0000 18.250 1.7518 0.08863 0.08419 -0.0951 0.1734 1.0000