GOE 620 AIRFOIL (goe620-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 620 AIRFOIL (goe620-il) Reynolds number: 200,000 Max Cl/Cd: 71.05 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe620-il-200000.txt Download as CSV file: xf-goe620-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 620 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
------ -------- --------- --------- -------- -------- --------
-10.750 0.1033 0.08996 0.08612 -0.1249 0.9306 0.1017
-10.500 0.1256 0.08708 0.08323 -0.1266 0.9264 0.1038
-10.250 -0.2121 0.04793 0.04339 -0.1620 0.9201 0.0722
-10.000 -0.2348 0.04491 0.04020 -0.1601 0.9070 0.0718
-9.750 -0.2481 0.04092 0.03588 -0.1602 0.8989 0.0715
-9.500 -0.2587 0.03827 0.03293 -0.1577 0.8891 0.0714
-9.250 -0.2505 0.03504 0.02926 -0.1581 0.8849 0.0715
-9.000 -0.2582 0.03369 0.02766 -0.1535 0.8747 0.0716
-8.750 -0.2440 0.03159 0.02518 -0.1528 0.8699 0.0720
-8.500 -0.2218 0.02977 0.02295 -0.1530 0.8668 0.0726
-8.250 -0.2183 0.02871 0.02182 -0.1494 0.8584 0.0733
-8.000 -0.1946 0.02760 0.02068 -0.1491 0.8539 0.0746
-7.750 -0.1659 0.02654 0.01952 -0.1496 0.8507 0.0761
-7.500 -0.1350 0.02538 0.01817 -0.1505 0.8481 0.0774
-7.250 -0.1300 0.02500 0.01768 -0.1466 0.8399 0.0782
-7.000 -0.1063 0.02413 0.01663 -0.1459 0.8354 0.0795
-6.750 -0.0769 0.02324 0.01551 -0.1462 0.8322 0.0810
-6.500 -0.0434 0.02221 0.01452 -0.1474 0.8297 0.0833
-6.250 -0.0349 0.02209 0.01442 -0.1440 0.8223 0.0849
-6.000 -0.0102 0.02155 0.01380 -0.1433 0.8175 0.0871
-5.750 0.0206 0.02092 0.01301 -0.1437 0.8141 0.0895
-5.500 0.0536 0.02006 0.01220 -0.1446 0.8114 0.0925
-5.250 0.0645 0.01999 0.01217 -0.1415 0.8043 0.0951
-5.000 0.0886 0.01965 0.01175 -0.1407 0.7993 0.0990
-4.750 0.1180 0.01900 0.01114 -0.1409 0.7957 0.1037
-4.500 0.1524 0.01849 0.01055 -0.1419 0.7927 0.1104
-4.250 0.1620 0.01835 0.01053 -0.1386 0.7855 0.1164
-4.000 0.1856 0.01794 0.01017 -0.1376 0.7803 0.1280
-3.750 0.2156 0.01738 0.00969 -0.1379 0.7766 0.1528
-3.500 0.2505 0.01699 0.00939 -0.1391 0.7735 0.1899
-3.250 0.2594 0.01715 0.00963 -0.1355 0.7655 0.2088
-3.000 0.2873 0.01701 0.00948 -0.1353 0.7606 0.2310
-2.750 0.3216 0.01680 0.00922 -0.1363 0.7568 0.2515
-2.500 0.3445 0.01680 0.00925 -0.1353 0.7513 0.2675
-2.250 0.3641 0.01680 0.00930 -0.1336 0.7446 0.2822
-2.000 0.3950 0.01663 0.00911 -0.1339 0.7400 0.2999
-1.750 0.4317 0.01645 0.00888 -0.1353 0.7364 0.3199
-1.500 0.4437 0.01660 0.00908 -0.1322 0.7284 0.3338
-1.250 0.4709 0.01651 0.00898 -0.1319 0.7229 0.3524
-1.000 0.5058 0.01629 0.00876 -0.1330 0.7188 0.3740
-0.750 0.5233 0.01634 0.00888 -0.1309 0.7117 0.3911
-0.500 0.5468 0.01623 0.00883 -0.1298 0.7053 0.4105
-0.250 0.5804 0.01602 0.00860 -0.1307 0.7007 0.4339
0.000 0.6009 0.01599 0.00867 -0.1291 0.6942 0.4559
0.250 0.6214 0.01589 0.00869 -0.1275 0.6871 0.4809
0.500 0.6535 0.01568 0.00851 -0.1281 0.6823 0.5153
0.750 0.6730 0.01564 0.00860 -0.1263 0.6756 0.5473
1.000 0.6929 0.01551 0.00860 -0.1245 0.6684 0.5849
1.250 0.7247 0.01516 0.00835 -0.1249 0.6631 0.6377
1.500 0.7368 0.01498 0.00846 -0.1215 0.6546 0.7017
1.750 0.8695 0.01424 0.00809 -0.1425 0.6451 1.0000
2.000 0.8837 0.01436 0.00815 -0.1398 0.6364 1.0000
2.250 0.9071 0.01438 0.00804 -0.1388 0.6293 1.0000
2.500 0.9283 0.01446 0.00803 -0.1374 0.6219 1.0000
2.750 0.9459 0.01456 0.00807 -0.1353 0.6139 1.0000
3.000 0.9744 0.01458 0.00794 -0.1353 0.6073 1.0000
3.250 0.9855 0.01476 0.00813 -0.1320 0.5983 1.0000
3.500 1.0122 0.01479 0.00802 -0.1316 0.5912 1.0000
3.750 1.0251 0.01499 0.00821 -0.1287 0.5824 1.0000
4.000 1.0483 0.01508 0.00819 -0.1276 0.5746 1.0000
4.250 1.0643 0.01529 0.00837 -0.1253 0.5664 1.0000
4.500 1.0838 0.01544 0.00844 -0.1237 0.5583 1.0000
4.750 1.1032 0.01565 0.00860 -0.1220 0.5505 1.0000
5.000 1.1186 0.01587 0.00878 -0.1196 0.5422 1.0000
5.250 1.1411 0.01608 0.00890 -0.1186 0.5345 1.0000
5.500 1.1501 0.01634 0.00916 -0.1150 0.5262 1.0000
5.750 1.1766 0.01656 0.00925 -0.1148 0.5186 1.0000
6.000 1.1816 0.01687 0.00961 -0.1105 0.5103 1.0000
6.250 1.2037 0.01711 0.00974 -0.1095 0.5023 1.0000
6.500 1.2120 0.01746 0.01013 -0.1060 0.4940 1.0000
6.750 1.2291 0.01775 0.01035 -0.1041 0.4859 1.0000
7.000 1.2412 0.01812 0.01073 -0.1015 0.4775 1.0000
7.250 1.2545 0.01847 0.01104 -0.0990 0.4688 1.0000
7.500 1.2674 0.01888 0.01143 -0.0966 0.4604 1.0000
7.750 1.2793 0.01930 0.01184 -0.0941 0.4518 1.0000
8.000 1.2940 0.01974 0.01225 -0.0921 0.4437 1.0000
8.250 1.3039 0.02024 0.01277 -0.0894 0.4350 1.0000
8.500 1.3190 0.02072 0.01319 -0.0876 0.4270 1.0000
8.750 1.3279 0.02132 0.01383 -0.0849 0.4184 1.0000
9.000 1.3435 0.02183 0.01427 -0.0833 0.4104 1.0000
9.250 1.3502 0.02255 0.01505 -0.0805 0.4015 1.0000
9.500 1.3657 0.02311 0.01552 -0.0790 0.3936 1.0000
9.750 1.3722 0.02393 0.01642 -0.0764 0.3850 1.0000
10.000 1.3877 0.02453 0.01692 -0.0749 0.3777 1.0000
10.250 1.3943 0.02545 0.01793 -0.0725 0.3696 1.0000
10.500 1.4067 0.02618 0.01862 -0.0709 0.3623 1.0000
10.750 1.4178 0.02703 0.01949 -0.0691 0.3555 1.0000
11.000 1.4277 0.02793 0.02042 -0.0673 0.3486 1.0000
11.250 1.4444 0.02858 0.02098 -0.0663 0.3425 1.0000
11.500 1.4503 0.02971 0.02224 -0.0642 0.3360 1.0000
11.750 1.4602 0.03067 0.02318 -0.0626 0.3294 1.0000
12.000 1.4718 0.03160 0.02410 -0.0612 0.3233 1.0000
12.250 1.4787 0.03279 0.02539 -0.0595 0.3172 1.0000
12.500 1.4899 0.03375 0.02632 -0.0582 0.3112 1.0000
12.750 1.4989 0.03490 0.02752 -0.0567 0.3055 1.0000
13.000 1.5052 0.03623 0.02894 -0.0552 0.2996 1.0000
13.250 1.5167 0.03724 0.02990 -0.0540 0.2939 1.0000
13.500 1.5223 0.03870 0.03145 -0.0525 0.2881 1.0000
13.750 1.5268 0.04025 0.03307 -0.0511 0.2819 1.0000
14.000 1.5394 0.04121 0.03393 -0.0501 0.2758 1.0000
14.250 1.5374 0.04336 0.03626 -0.0485 0.2693 1.0000
14.500 1.5417 0.04502 0.03793 -0.0472 0.2624 1.0000
14.750 1.5441 0.04690 0.03986 -0.0460 0.2555 1.0000
15.000 1.5433 0.04911 0.04213 -0.0447 0.2477 1.0000
15.250 1.5450 0.05114 0.04415 -0.0435 0.2401 1.0000
15.500 1.5410 0.05379 0.04686 -0.0424 0.2315 1.0000
15.750 1.5385 0.05635 0.04943 -0.0414 0.2229 1.0000
16.000 1.5361 0.05897 0.05206 -0.0405 0.2149 1.0000
16.250 1.5329 0.06176 0.05490 -0.0398 0.2071 1.0000
16.500 1.5304 0.06455 0.05769 -0.0391 0.2000 1.0000
16.750 1.5298 0.06717 0.06034 -0.0386 0.1939 1.0000
17.000 1.5275 0.07011 0.06337 -0.0383 0.1879 1.0000
17.250 1.5302 0.07235 0.06553 -0.0378 0.1831 1.0000
17.500 1.5288 0.07526 0.06857 -0.0376 0.1784 1.0000
17.750 1.5286 0.07806 0.07145 -0.0375 0.1741 1.0000
18.000 1.5314 0.08039 0.07376 -0.0373 0.1704 1.0000
18.250 1.5346 0.08272 0.07612 -0.0371 0.1669 1.0000
18.500 1.5340 0.08560 0.07913 -0.0372 0.1637 1.0000
18.750 1.5339 0.08845 0.08205 -0.0373 0.1602 1.0000
19.000 1.5380 0.09063 0.08421 -0.0373 0.1571 1.0000
19.250 1.5416 0.09290 0.08651 -0.0373 0.1540 1.0000
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Polar data table (+)
Polar graphs
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