XFOIL Version 6.96 Calculated polar for: GOE 498 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 ------ -------- --------- --------- -------- -------- -------- -19.000 -0.7437 0.11358 0.11101 -0.0695 1.0000 0.0305 -18.750 -0.7648 0.10667 0.10402 -0.0733 1.0000 0.0308 -18.500 -0.7819 0.10065 0.09792 -0.0765 1.0000 0.0310 -18.250 -0.7986 0.09482 0.09201 -0.0797 1.0000 0.0313 -18.000 -0.8150 0.08921 0.08633 -0.0826 1.0000 0.0315 -17.750 -0.8311 0.08379 0.08083 -0.0854 1.0000 0.0318 -17.500 -0.8465 0.07863 0.07558 -0.0880 1.0000 0.0320 -17.250 -0.8593 0.07411 0.07100 -0.0901 1.0000 0.0322 -17.000 -0.8736 0.06954 0.06635 -0.0922 1.0000 0.0324 -16.750 -0.8882 0.06520 0.06194 -0.0939 1.0000 0.0325 -16.500 -0.9056 0.06088 0.05754 -0.0954 1.0000 0.0327 -16.250 -0.9252 0.05701 0.05361 -0.0961 1.0000 0.0327 -16.000 -0.9375 0.05281 0.04933 -0.0987 0.9995 0.0329 -15.750 -0.9389 0.04775 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0.6022 0.2554 -1.250 0.5271 0.00772 0.00195 -0.1433 0.5942 0.2709 -1.000 0.5540 0.00773 0.00196 -0.1429 0.5855 0.2837 -0.750 0.5804 0.00778 0.00198 -0.1424 0.5767 0.2939 -0.500 0.6075 0.00778 0.00201 -0.1420 0.5686 0.3052 0.000 0.6607 0.00786 0.00207 -0.1411 0.5526 0.3263 0.250 0.6867 0.00794 0.00211 -0.1406 0.5440 0.3344 0.500 0.7134 0.00797 0.00216 -0.1401 0.5366 0.3450 0.750 0.7398 0.00803 0.00221 -0.1397 0.5288 0.3549 1.000 0.7654 0.00809 0.00227 -0.1391 0.5212 0.3675 1.250 0.7922 0.00813 0.00233 -0.1387 0.5141 0.3795 1.500 0.8175 0.00820 0.00240 -0.1380 0.5062 0.3940 1.750 0.8437 0.00824 0.00247 -0.1375 0.4990 0.4094 2.000 0.8692 0.00831 0.00255 -0.1369 0.4906 0.4254 2.250 0.8942 0.00839 0.00264 -0.1362 0.4824 0.4434 2.500 0.9193 0.00846 0.00274 -0.1355 0.4725 0.4639 2.750 0.9437 0.00855 0.00285 -0.1347 0.4638 0.4880 3.000 0.9684 0.00863 0.00297 -0.1340 0.4544 0.5110 3.250 0.9923 0.00874 0.00309 -0.1331 0.4450 0.5317 3.500 1.0160 0.00886 0.00322 -0.1321 0.4345 0.5534 3.750 1.0395 0.00898 0.00335 -0.1312 0.4252 0.5742 4.000 1.0615 0.00912 0.00349 -0.1299 0.4143 0.5938 4.250 1.0835 0.00924 0.00362 -0.1287 0.4046 0.6117 4.500 1.1031 0.00940 0.00379 -0.1270 0.3939 0.6336 4.750 1.1246 0.00951 0.00394 -0.1256 0.3842 0.6574 5.000 1.1439 0.00966 0.00414 -0.1239 0.3741 0.6939 5.250 1.1595 0.00957 0.00438 -0.1213 0.3647 0.8248 5.500 1.1912 0.00962 0.00461 -0.1222 0.3550 1.0000 5.750 1.2111 0.00988 0.00481 -0.1207 0.3452 1.0000 6.000 1.2312 0.01013 0.00502 -0.1192 0.3355 1.0000 6.250 1.2509 0.01040 0.00524 -0.1176 0.3271 1.0000 6.500 1.2707 0.01066 0.00547 -0.1161 0.3183 1.0000 6.750 1.2892 0.01098 0.00573 -0.1144 0.3086 1.0000 7.000 1.3090 0.01125 0.00597 -0.1130 0.2995 1.0000 7.250 1.3256 0.01163 0.00629 -0.1110 0.2876 1.0000 7.500 1.3421 0.01204 0.00662 -0.1091 0.2731 1.0000 7.750 1.3583 0.01246 0.00697 -0.1072 0.2585 1.0000 8.000 1.3714 0.01301 0.00741 -0.1048 0.2392 1.0000 8.250 1.3784 0.01384 0.00806 -0.1015 0.2088 1.0000 8.500 1.3868 0.01463 0.00873 -0.0986 0.1882 1.0000 8.750 1.3984 0.01531 0.00934 -0.0962 0.1776 1.0000 9.000 1.4131 0.01585 0.00987 -0.0943 0.1726 1.0000 9.250 1.4264 0.01648 0.01048 -0.0923 0.1674 1.0000 9.500 1.4422 0.01701 0.01102 -0.0907 0.1642 1.0000 9.750 1.4582 0.01754 0.01156 -0.0892 0.1618 1.0000 10.000 1.4735 0.01812 0.01215 -0.0876 0.1592 1.0000 10.250 1.4866 0.01882 0.01286 -0.0858 0.1561 1.0000 10.500 1.4994 0.01957 0.01361 -0.0840 0.1528 1.0000 10.750 1.5141 0.02022 0.01429 -0.0825 0.1506 1.0000 11.000 1.5306 0.02080 0.01491 -0.0813 0.1489 1.0000 11.250 1.5455 0.02148 0.01562 -0.0799 0.1464 1.0000 11.500 1.5581 0.02232 0.01646 -0.0784 0.1433 1.0000 11.750 1.5689 0.02329 0.01745 -0.0767 0.1398 1.0000 12.000 1.5823 0.02412 0.01831 -0.0753 0.1370 1.0000 12.250 1.5975 0.02486 0.01909 -0.0742 0.1339 1.0000 12.500 1.6083 0.02592 0.02014 -0.0728 0.1286 1.0000 12.750 1.6191 0.02701 0.02124 -0.0714 0.1230 1.0000 13.000 1.6267 0.02837 0.02255 -0.0699 0.1124 1.0000 13.250 1.6220 0.03070 0.02473 -0.0677 0.0907 1.0000 13.500 1.6162 0.03327 0.02724 -0.0656 0.0792 1.0000 13.750 1.6162 0.03547 0.02944 -0.0641 0.0732 1.0000 14.000 1.6166 0.03772 0.03170 -0.0627 0.0689 1.0000 14.250 1.6199 0.03979 0.03381 -0.0617 0.0653 1.0000 14.500 1.6197 0.04223 0.03626 -0.0606 0.0619 1.0000 14.750 1.6239 0.04429 0.03837 -0.0597 0.0589 1.0000 15.000 1.6247 0.04675 0.04085 -0.0589 0.0563 1.0000 15.250 1.6272 0.04912 0.04327 -0.0583 0.0538 1.0000 15.500 1.6287 0.05162 0.04581 -0.0577 0.0518 1.0000 15.750 1.6274 0.05447 0.04869 -0.0572 0.0495 1.0000 16.000 1.6300 0.05697 0.05125 -0.0568 0.0481 1.0000 16.250 1.6306 0.05976 0.05408 -0.0566 0.0466 1.0000 16.500 1.6291 0.06283 0.05719 -0.0564 0.0451 1.0000 16.750 1.6265 0.06609 0.06051 -0.0563 0.0439 1.0000 17.000 1.6275 0.06900 0.06350 -0.0564 0.0430 1.0000 17.250 1.6278 0.07202 0.06659 -0.0565 0.0421 1.0000 17.500 1.6257 0.07541 0.07003 -0.0568 0.0412 1.0000 17.750 1.6217 0.07911 0.07380 -0.0572 0.0404 1.0000 18.000 1.6162 0.08307 0.07782 -0.0578 0.0396 1.0000 18.250 1.6104 0.08715 0.08197 -0.0585 0.0389 1.0000