GOE 390 AIRFOIL (goe390-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 390 AIRFOIL (goe390-il) Reynolds number: 500,000 Max Cl/Cd: 85.22 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe390-il-500000.txt Download as CSV file: xf-goe390-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 390 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4920 0.04151 0.03750 -0.1437 0.8712 0.0401
-13.250 -0.5089 0.03582 0.03147 -0.1501 0.8572 0.0402
-13.000 -0.5126 0.03282 0.02826 -0.1526 0.8454 0.0403
-12.750 -0.5106 0.03092 0.02617 -0.1527 0.8359 0.0405
-12.500 -0.5067 0.02952 0.02462 -0.1517 0.8269 0.0407
-12.250 -0.4961 0.02825 0.02316 -0.1511 0.8190 0.0410
-12.000 -0.4826 0.02707 0.02185 -0.1505 0.8118 0.0413
-11.750 -0.4669 0.02604 0.02067 -0.1499 0.8044 0.0417
-11.500 -0.4499 0.02509 0.01954 -0.1493 0.7973 0.0422
-11.250 -0.4319 0.02411 0.01843 -0.1487 0.7904 0.0426
-11.000 -0.4128 0.02321 0.01735 -0.1480 0.7835 0.0430
-10.750 -0.3923 0.02244 0.01638 -0.1474 0.7770 0.0433
-10.500 -0.3724 0.02138 0.01524 -0.1468 0.7710 0.0437
-10.250 -0.3502 0.02065 0.01448 -0.1463 0.7645 0.0442
-10.000 -0.3267 0.02013 0.01389 -0.1458 0.7582 0.0447
-9.750 -0.3028 0.01964 0.01335 -0.1454 0.7517 0.0452
-9.500 -0.2788 0.01913 0.01279 -0.1449 0.7445 0.0458
-9.250 -0.2546 0.01865 0.01218 -0.1444 0.7376 0.0465
-9.000 -0.2302 0.01816 0.01159 -0.1440 0.7307 0.0472
-8.750 -0.2055 0.01769 0.01101 -0.1435 0.7234 0.0478
-8.500 -0.1814 0.01712 0.01035 -0.1430 0.7170 0.0486
-8.250 -0.1560 0.01675 0.00997 -0.1426 0.7114 0.0494
-8.000 -0.1300 0.01644 0.00965 -0.1423 0.7055 0.0503
-7.750 -0.1038 0.01615 0.00929 -0.1420 0.6997 0.0514
-7.500 -0.0773 0.01591 0.00890 -0.1417 0.6943 0.0527
-7.250 -0.0516 0.01550 0.00851 -0.1413 0.6896 0.0540
-7.000 -0.0249 0.01529 0.00829 -0.1411 0.6843 0.0553
-6.750 0.0019 0.01508 0.00802 -0.1408 0.6791 0.0569
-6.500 0.0289 0.01489 0.00769 -0.1405 0.6739 0.0586
-6.250 0.0552 0.01459 0.00745 -0.1403 0.6693 0.0603
-6.000 0.0825 0.01443 0.00726 -0.1401 0.6644 0.0625
-5.750 0.1094 0.01421 0.00696 -0.1398 0.6597 0.0649
-5.500 0.1365 0.01405 0.00677 -0.1396 0.6551 0.0671
-5.250 0.1642 0.01395 0.00662 -0.1395 0.6508 0.0700
-5.000 0.1904 0.01364 0.00634 -0.1392 0.6461 0.0726
-4.750 0.2176 0.01350 0.00617 -0.1389 0.6411 0.0756
-4.500 0.2442 0.01329 0.00589 -0.1387 0.6363 0.0785
-4.250 0.2712 0.01311 0.00571 -0.1385 0.6319 0.0814
-4.000 0.2984 0.01298 0.00555 -0.1383 0.6275 0.0841
-3.750 0.3244 0.01268 0.00529 -0.1379 0.6228 0.0872
-3.500 0.3515 0.01255 0.00513 -0.1377 0.6181 0.0903
-3.250 0.3788 0.01245 0.00497 -0.1375 0.6132 0.0936
-3.000 0.4052 0.01227 0.00484 -0.1372 0.6085 0.0974
-2.750 0.4320 0.01215 0.00472 -0.1369 0.6032 0.1011
-2.500 0.4588 0.01205 0.00463 -0.1366 0.5979 0.1063
-2.250 0.4860 0.01202 0.00459 -0.1365 0.5928 0.1132
-2.000 0.5128 0.01193 0.00458 -0.1362 0.5878 0.1233
-1.750 0.5396 0.01188 0.00457 -0.1359 0.5821 0.1366
-1.500 0.5663 0.01188 0.00455 -0.1356 0.5764 0.1511
-1.250 0.5928 0.01185 0.00455 -0.1353 0.5706 0.1633
-1.000 0.6191 0.01182 0.00452 -0.1349 0.5640 0.1729
-0.750 0.6447 0.01180 0.00449 -0.1345 0.5574 0.1825
-0.500 0.6707 0.01181 0.00449 -0.1341 0.5511 0.1903
-0.250 0.6964 0.01178 0.00448 -0.1336 0.5438 0.1987
0.000 0.7211 0.01183 0.00448 -0.1330 0.5365 0.2068
0.250 0.7464 0.01180 0.00452 -0.1325 0.5289 0.2189
0.500 0.7705 0.01182 0.00454 -0.1319 0.5206 0.2340
0.750 0.7946 0.01184 0.00461 -0.1312 0.5130 0.2587
1.000 0.8185 0.01181 0.00468 -0.1305 0.5049 0.3001
1.250 0.8408 0.01181 0.00478 -0.1296 0.4972 0.3569
1.500 0.8643 0.01166 0.00493 -0.1290 0.4897 0.4572
1.750 0.8858 0.01163 0.00510 -0.1280 0.4823 0.5539
2.000 0.9075 0.01160 0.00527 -0.1269 0.4759 0.6298
2.250 0.9249 0.01133 0.00550 -0.1248 0.4698 0.7966
2.500 0.9639 0.01139 0.00578 -0.1269 0.4628 1.0000
2.750 0.9840 0.01159 0.00593 -0.1255 0.4575 1.0000
3.000 1.0048 0.01179 0.00608 -0.1242 0.4522 1.0000
3.250 1.0246 0.01205 0.00626 -0.1229 0.4470 1.0000
3.500 1.0447 0.01236 0.00648 -0.1216 0.4418 1.0000
3.750 1.0671 0.01256 0.00667 -0.1208 0.4375 1.0000
4.000 1.0886 0.01281 0.00688 -0.1198 0.4328 1.0000
4.250 1.1093 0.01312 0.00712 -0.1188 0.4284 1.0000
4.500 1.1302 0.01349 0.00740 -0.1178 0.4237 1.0000
4.750 1.1523 0.01372 0.00765 -0.1170 0.4204 1.0000
5.000 1.1742 0.01399 0.00791 -0.1162 0.4166 1.0000
5.250 1.1953 0.01431 0.00819 -0.1154 0.4128 1.0000
5.500 1.2156 0.01469 0.00851 -0.1144 0.4089 1.0000
5.750 1.2369 0.01508 0.00884 -0.1136 0.4049 1.0000
6.000 1.2581 0.01538 0.00917 -0.1128 0.4019 1.0000
6.250 1.2789 0.01572 0.00952 -0.1120 0.3986 1.0000
6.500 1.2991 0.01610 0.00988 -0.1111 0.3951 1.0000
6.750 1.3186 0.01653 0.01028 -0.1102 0.3915 1.0000
7.000 1.3391 0.01701 0.01067 -0.1094 0.3872 1.0000
7.250 1.3583 0.01741 0.01113 -0.1085 0.3846 1.0000
7.500 1.3779 0.01783 0.01158 -0.1077 0.3815 1.0000
7.750 1.3968 0.01829 0.01205 -0.1068 0.3781 1.0000
8.000 1.4147 0.01882 0.01256 -0.1058 0.3745 1.0000
8.250 1.4325 0.01940 0.01309 -0.1048 0.3706 1.0000
8.500 1.4507 0.01994 0.01366 -0.1040 0.3674 1.0000
8.750 1.4684 0.02050 0.01427 -0.1031 0.3643 1.0000
9.000 1.4857 0.02111 0.01489 -0.1022 0.3608 1.0000
9.250 1.5017 0.02179 0.01557 -0.1012 0.3572 1.0000
9.500 1.5171 0.02252 0.01626 -0.1001 0.3533 1.0000
9.750 1.5330 0.02325 0.01702 -0.0992 0.3498 1.0000
10.000 1.5487 0.02400 0.01782 -0.0983 0.3462 1.0000
10.250 1.5634 0.02482 0.01867 -0.0974 0.3424 1.0000
10.500 1.5770 0.02571 0.01956 -0.0964 0.3386 1.0000
10.750 1.5901 0.02664 0.02043 -0.0952 0.3345 1.0000
11.000 1.6040 0.02759 0.02147 -0.0944 0.3311 1.0000
11.250 1.6176 0.02857 0.02249 -0.0935 0.3270 1.0000
11.500 1.6286 0.02972 0.02366 -0.0925 0.3227 1.0000
11.750 1.6385 0.03094 0.02483 -0.0913 0.3182 1.0000
12.000 1.6505 0.03212 0.02609 -0.0905 0.3144 1.0000
12.250 1.6622 0.03332 0.02734 -0.0897 0.3101 1.0000
12.500 1.6708 0.03475 0.02877 -0.0886 0.3057 1.0000
12.750 1.6783 0.03624 0.03022 -0.0875 0.3012 1.0000
13.000 1.6891 0.03762 0.03168 -0.0868 0.2973 1.0000
13.250 1.6978 0.03914 0.03325 -0.0860 0.2927 1.0000
13.500 1.7033 0.04092 0.03501 -0.0849 0.2882 1.0000
13.750 1.7098 0.04263 0.03674 -0.0840 0.2838 1.0000
14.000 1.7178 0.04430 0.03848 -0.0833 0.2795 1.0000
14.250 1.7232 0.04620 0.04039 -0.0825 0.2750 1.0000
14.500 1.7265 0.04823 0.04239 -0.0815 0.2706 1.0000
14.750 1.7332 0.05005 0.04429 -0.0808 0.2670 1.0000
15.000 1.7397 0.05191 0.04620 -0.0802 0.2631 1.0000
15.250 1.7428 0.05408 0.04837 -0.0794 0.2592 1.0000
15.500 1.7463 0.05612 0.05038 -0.0786 0.2552 1.0000
15.750 1.7510 0.05822 0.05257 -0.0780 0.2520 1.0000
16.000 1.7555 0.06036 0.05478 -0.0775 0.2484 1.0000
16.250 1.7581 0.06263 0.05706 -0.0769 0.2448 1.0000
16.500 1.7603 0.06489 0.05930 -0.0763 0.2412 1.0000
16.750 1.7652 0.06691 0.06137 -0.0758 0.2381 1.0000
17.000 1.7669 0.06943 0.06399 -0.0754 0.2351 1.0000
17.250 1.7687 0.07190 0.06650 -0.0751 0.2317 1.0000
17.500 1.7698 0.07439 0.06898 -0.0747 0.2283 1.0000
17.750 1.7732 0.07651 0.07108 -0.0742 0.2246 1.0000
18.000 1.7724 0.07940 0.07409 -0.0741 0.2218 1.0000
18.250 1.7703 0.08242 0.07719 -0.0739 0.2185 1.0000
18.500 1.7706 0.08509 0.07988 -0.0738 0.2152 1.0000
18.750 1.7740 0.08727 0.08202 -0.0735 0.2117 1.0000
19.000 1.7728 0.09020 0.08504 -0.0735 0.2091 1.0000
19.250 1.7717 0.09314 0.08808 -0.0736 0.2065 1.0000
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Polar data table (+)
Polar graphs
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