GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 482 AIRFOIL (goe482-il) Reynolds number: 200,000 Max Cl/Cd: 71.23 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe482-il-200000.txt Download as CSV file: xf-goe482-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 482 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.2056 0.10264 0.09854 -0.1321 0.8728 0.0631
-11.000 0.2169 0.10029 0.09612 -0.1334 0.8650 0.0652
-10.750 0.1949 0.10035 0.09616 -0.1373 0.8550 0.0685
-10.500 0.2115 0.09620 0.09194 -0.1377 0.8486 0.0691
-10.250 0.2320 0.09324 0.08895 -0.1368 0.8409 0.0701
-10.000 0.2469 0.09105 0.08668 -0.1371 0.8342 0.0714
-9.750 0.2556 0.08919 0.08481 -0.1373 0.8265 0.0738
-9.500 0.2311 0.08915 0.08476 -0.1410 0.8175 0.0780
-9.250 0.2376 0.08582 0.08141 -0.1413 0.8107 0.0787
-9.000 0.2605 0.08295 0.07850 -0.1399 0.8034 0.0795
-8.750 0.2793 0.08081 0.07627 -0.1395 0.7971 0.0811
-8.500 0.2881 0.07916 0.07464 -0.1391 0.7888 0.0831
-8.250 0.2936 0.07741 0.07285 -0.1396 0.7815 0.0862
-8.000 0.2517 0.07668 0.07222 -0.1436 0.7718 0.0893
-7.750 0.2813 0.07319 0.06866 -0.1419 0.7656 0.0902
-7.500 0.3028 0.07114 0.06651 -0.1410 0.7597 0.0914
-7.250 0.3145 0.06961 0.06500 -0.1399 0.7507 0.0933
-7.000 0.3233 0.06789 0.06322 -0.1399 0.7439 0.0962
-6.750 0.2817 0.06637 0.06182 -0.1489 0.7335 0.1015
-6.500 0.2996 0.06367 0.05906 -0.1444 0.7276 0.1023
-6.250 0.3167 0.06199 0.05735 -0.1419 0.7204 0.1033
-6.000 0.3317 0.06048 0.05581 -0.1406 0.7125 0.1049
-5.750 0.3362 0.05579 0.05099 -0.1590 0.7053 0.1152
-5.500 0.3472 0.05430 0.04955 -0.1538 0.6972 0.1160
-5.250 0.3639 0.05302 0.04820 -0.1507 0.6912 0.1170
-5.000 0.3931 0.04822 0.04310 -0.1687 0.6827 0.1299
-4.750 0.4072 0.04602 0.04096 -0.1655 0.6763 0.1308
-4.500 0.4234 0.04493 0.03988 -0.1629 0.6699 0.1318
-4.250 0.4399 0.04393 0.03888 -0.1610 0.6623 0.1333
-4.000 0.5016 0.02783 0.02133 -0.1878 0.6578 0.1029
-3.750 0.5299 0.02595 0.01926 -0.1889 0.6512 0.0984
-3.500 0.5607 0.02375 0.01670 -0.1908 0.6444 0.0957
-3.250 0.5930 0.02233 0.01486 -0.1923 0.6391 0.0957
-3.000 0.6210 0.02129 0.01360 -0.1928 0.6321 0.0956
-2.750 0.6508 0.02038 0.01242 -0.1933 0.6260 0.0955
-2.500 0.6813 0.01973 0.01149 -0.1939 0.6209 0.0961
-2.250 0.7080 0.01924 0.01090 -0.1938 0.6141 0.0970
-2.000 0.7369 0.01883 0.01033 -0.1940 0.6086 0.0985
-1.750 0.7667 0.01860 0.00989 -0.1943 0.6036 0.1005
-1.500 0.7929 0.01824 0.00951 -0.1941 0.5975 0.1023
-1.250 0.8209 0.01787 0.00913 -0.1941 0.5922 0.1045
-1.000 0.8511 0.01772 0.00887 -0.1946 0.5876 0.1075
-0.750 0.8764 0.01762 0.00883 -0.1942 0.5819 0.1108
-0.500 0.9040 0.01755 0.00871 -0.1941 0.5767 0.1152
-0.250 0.9334 0.01743 0.00858 -0.1945 0.5723 0.1226
0.000 0.9610 0.01743 0.00858 -0.1945 0.5675 0.1319
0.250 0.9876 0.01736 0.00861 -0.1944 0.5621 0.1503
0.500 1.0173 0.01697 0.00861 -0.1951 0.5573 0.2666
0.750 1.0475 0.01715 0.00885 -0.1956 0.5532 0.3811
1.000 1.0712 0.01733 0.00914 -0.1950 0.5483 0.4193
1.250 1.0969 0.01745 0.00933 -0.1946 0.5434 0.4513
1.500 1.1244 0.01756 0.00947 -0.1946 0.5390 0.4867
1.750 1.1523 0.01778 0.00970 -0.1947 0.5348 0.5245
2.000 1.1747 0.01796 0.01002 -0.1938 0.5297 0.5598
2.250 1.2000 0.01809 0.01023 -0.1934 0.5250 0.6041
2.500 1.2267 0.01814 0.01039 -0.1932 0.5210 0.6631
2.750 1.2496 0.01808 0.01059 -0.1921 0.5172 0.8004
3.000 1.2714 0.01816 0.01080 -0.1911 0.5123 1.0000
3.250 1.2975 0.01844 0.01099 -0.1909 0.5076 1.0000
3.500 1.3262 0.01870 0.01110 -0.1912 0.5035 1.0000
3.750 1.3528 0.01909 0.01140 -0.1912 0.4993 1.0000
4.000 1.3737 0.01944 0.01178 -0.1903 0.4944 1.0000
4.250 1.3987 0.01974 0.01203 -0.1899 0.4900 1.0000
4.500 1.4268 0.02003 0.01220 -0.1902 0.4862 1.0000
4.750 1.4535 0.02046 0.01256 -0.1902 0.4824 1.0000
5.000 1.4719 0.02086 0.01304 -0.1888 0.4778 1.0000
5.250 1.4948 0.02119 0.01335 -0.1882 0.4734 1.0000
5.500 1.5218 0.02146 0.01354 -0.1883 0.4695 1.0000
5.750 1.5497 0.02187 0.01385 -0.1885 0.4658 1.0000
6.000 1.5644 0.02233 0.01443 -0.1866 0.4612 1.0000
6.250 1.5851 0.02272 0.01484 -0.1857 0.4570 1.0000
6.500 1.6103 0.02304 0.01511 -0.1855 0.4534 1.0000
6.750 1.6405 0.02340 0.01536 -0.1862 0.4502 1.0000
7.000 1.6548 0.02399 0.01606 -0.1843 0.4463 1.0000
7.250 1.6701 0.02450 0.01666 -0.1826 0.4422 1.0000
7.500 1.6910 0.02488 0.01704 -0.1817 0.4385 1.0000
7.750 1.7179 0.02518 0.01727 -0.1819 0.4351 1.0000
8.000 1.7435 0.02567 0.01774 -0.1819 0.4318 1.0000
8.250 1.7494 0.02638 0.01861 -0.1787 0.4280 1.0000
8.500 1.7617 0.02695 0.01925 -0.1766 0.4244 1.0000
8.750 1.7811 0.02739 0.01971 -0.1756 0.4212 1.0000
9.000 1.8093 0.02774 0.02001 -0.1760 0.4184 1.0000
9.250 1.8357 0.02829 0.02055 -0.1763 0.4154 1.0000
9.500 1.8276 0.02924 0.02168 -0.1711 0.4117 1.0000
9.750 1.8326 0.02999 0.02253 -0.1681 0.4080 1.0000
10.000 1.8499 0.03040 0.02295 -0.1669 0.4044 1.0000
10.250 1.8861 0.03032 0.02272 -0.1683 0.4002 1.0000
10.500 1.8701 0.03166 0.02427 -0.1627 0.3960 1.0000
10.750 1.8668 0.03270 0.02542 -0.1590 0.3912 1.0000
11.000 1.8851 0.03284 0.02549 -0.1580 0.3862 1.0000
11.250 1.8964 0.03359 0.02626 -0.1564 0.3818 1.0000
11.500 1.8846 0.03541 0.02826 -0.1524 0.3775 1.0000
11.750 1.8902 0.03650 0.02942 -0.1505 0.3733 1.0000
12.000 1.9117 0.03674 0.02961 -0.1500 0.3692 1.0000
12.250 1.9128 0.03825 0.03121 -0.1478 0.3649 1.0000
12.500 1.9011 0.04057 0.03371 -0.1447 0.3605 1.0000
12.750 1.9072 0.04175 0.03492 -0.1432 0.3557 1.0000
13.000 1.9345 0.04165 0.03470 -0.1432 0.3511 1.0000
13.250 1.9115 0.04511 0.03842 -0.1399 0.3470 1.0000
13.500 1.9053 0.04751 0.04095 -0.1379 0.3424 1.0000
13.750 1.9185 0.04835 0.04178 -0.1371 0.3377 1.0000
14.000 1.9171 0.05054 0.04405 -0.1356 0.3329 1.0000
14.250 1.8994 0.05436 0.04806 -0.1337 0.3279 1.0000
14.500 1.9041 0.05609 0.04981 -0.1328 0.3227 1.0000
14.750 1.9082 0.05802 0.05178 -0.1319 0.3176 1.0000
15.000 1.8857 0.06296 0.05693 -0.1306 0.3125 1.0000
15.250 1.8882 0.06517 0.05918 -0.1299 0.3068 1.0000
15.500 1.8817 0.06857 0.06266 -0.1293 0.3009 1.0000
15.750 1.8588 0.07422 0.06850 -0.1288 0.2949 1.0000
16.000 1.8716 0.07528 0.06948 -0.1285 0.2879 1.0000
16.250 1.8376 0.08287 0.07734 -0.1286 0.2821 1.0000
16.500 1.8376 0.08582 0.08029 -0.1286 0.2748 1.0000
16.750 1.8129 0.09250 0.08716 -0.1291 0.2683 1.0000
17.000 1.8066 0.09652 0.09118 -0.1295 0.2594 1.0000
17.250 1.7790 0.10397 0.09884 -0.1306 0.2526 1.0000
17.500 1.7764 0.10754 0.10238 -0.1311 0.2430 1.0000
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