GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 430 AIRFOIL (goe430-il) Reynolds number: 200,000 Max Cl/Cd: 83.79 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe430-il-200000.txt Download as CSV file: xf-goe430-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 430 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3832 0.10426 0.10077 -0.0439 0.9956 0.1047
-9.000 -0.3520 0.10154 0.09802 -0.0426 0.9946 0.1058
-8.750 -0.4834 0.04891 0.04485 -0.1024 0.9722 0.0800
-8.500 -0.4636 0.03824 0.03335 -0.1171 0.9666 0.0799
-8.250 -0.4358 0.03351 0.02802 -0.1230 0.9613 0.0807
-8.000 -0.4013 0.03052 0.02482 -0.1271 0.9584 0.0822
-7.750 -0.3622 0.02867 0.02277 -0.1308 0.9562 0.0835
-7.500 -0.3288 0.02713 0.02102 -0.1332 0.9525 0.0847
-7.250 -0.2987 0.02580 0.01949 -0.1347 0.9472 0.0861
-7.000 -0.2601 0.02457 0.01802 -0.1376 0.9440 0.0882
-6.750 -0.2174 0.02331 0.01650 -0.1410 0.9417 0.0904
-6.500 -0.1723 0.02205 0.01498 -0.1448 0.9400 0.0921
-6.250 -0.1459 0.02107 0.01399 -0.1449 0.9324 0.0941
-6.000 -0.1039 0.02030 0.01320 -0.1478 0.9289 0.0970
-5.750 -0.0598 0.01956 0.01237 -0.1509 0.9264 0.1011
-5.500 -0.0167 0.01868 0.01139 -0.1538 0.9242 0.1054
-5.250 0.0101 0.01824 0.01099 -0.1536 0.9160 0.1093
-5.000 0.0480 0.01766 0.01034 -0.1553 0.9116 0.1158
-4.750 0.0869 0.01699 0.00971 -0.1572 0.9084 0.1245
-4.500 0.1144 0.01663 0.00935 -0.1571 0.9006 0.1364
-4.250 0.1475 0.01614 0.00889 -0.1580 0.8952 0.1541
-4.000 0.1825 0.01564 0.00838 -0.1592 0.8915 0.1714
-3.750 0.2089 0.01541 0.00815 -0.1588 0.8831 0.1836
-3.500 0.2405 0.01513 0.00782 -0.1593 0.8774 0.1955
-3.250 0.2726 0.01478 0.00752 -0.1598 0.8727 0.2067
-3.000 0.2988 0.01462 0.00737 -0.1593 0.8632 0.2165
-2.750 0.3306 0.01434 0.00705 -0.1596 0.8578 0.2276
-2.500 0.3574 0.01418 0.00696 -0.1592 0.8484 0.2389
-2.250 0.3880 0.01390 0.00668 -0.1593 0.8418 0.2520
-2.000 0.4155 0.01375 0.00657 -0.1590 0.8325 0.2674
-1.750 0.4457 0.01349 0.00634 -0.1591 0.8253 0.2876
-1.500 0.4735 0.01331 0.00620 -0.1589 0.8156 0.3123
-1.250 0.5037 0.01297 0.00596 -0.1590 0.8081 0.3415
-1.000 0.5312 0.01281 0.00589 -0.1587 0.7976 0.3705
-0.750 0.5610 0.01262 0.00572 -0.1587 0.7895 0.3997
-0.500 0.5885 0.01251 0.00569 -0.1583 0.7778 0.4255
-0.250 0.6165 0.01243 0.00562 -0.1580 0.7662 0.4517
0.000 0.6451 0.01232 0.00552 -0.1577 0.7551 0.4757
0.250 0.6732 0.01224 0.00544 -0.1574 0.7428 0.5010
0.500 0.7004 0.01220 0.00544 -0.1569 0.7292 0.5258
0.750 0.7278 0.01218 0.00545 -0.1565 0.7158 0.5521
1.000 0.7552 0.01221 0.00548 -0.1560 0.7033 0.5783
1.250 0.7829 0.01228 0.00553 -0.1556 0.6913 0.6060
1.500 0.8095 0.01237 0.00563 -0.1551 0.6779 0.6310
1.750 0.8360 0.01248 0.00574 -0.1545 0.6646 0.6554
2.000 0.8626 0.01259 0.00584 -0.1540 0.6518 0.6785
2.250 0.8891 0.01269 0.00592 -0.1535 0.6400 0.7025
2.500 0.9151 0.01277 0.00601 -0.1529 0.6282 0.7285
2.750 0.9404 0.01283 0.00616 -0.1522 0.6168 0.7575
3.000 0.9647 0.01285 0.00624 -0.1512 0.6062 0.7930
3.250 0.9837 0.01268 0.00625 -0.1488 0.5953 0.8749
3.500 1.0112 0.01277 0.00634 -0.1487 0.5836 1.0000
3.750 1.0395 0.01302 0.00647 -0.1488 0.5732 1.0000
4.000 1.0669 0.01325 0.00665 -0.1487 0.5633 1.0000
4.250 1.0945 0.01350 0.00686 -0.1487 0.5547 1.0000
4.500 1.1214 0.01373 0.00705 -0.1485 0.5454 1.0000
4.750 1.1476 0.01396 0.00726 -0.1481 0.5353 1.0000
5.000 1.1741 0.01422 0.00744 -0.1478 0.5260 1.0000
5.250 1.1993 0.01443 0.00769 -0.1472 0.5155 1.0000
5.500 1.2246 0.01468 0.00791 -0.1467 0.5051 1.0000
5.750 1.2496 0.01494 0.00814 -0.1461 0.4948 1.0000
6.000 1.2745 0.01521 0.00845 -0.1455 0.4851 1.0000
6.250 1.2990 0.01551 0.00870 -0.1448 0.4750 1.0000
6.500 1.3222 0.01580 0.00901 -0.1439 0.4625 1.0000
6.750 1.3448 0.01611 0.00934 -0.1429 0.4493 1.0000
7.000 1.3669 0.01646 0.00969 -0.1418 0.4358 1.0000
7.250 1.3878 0.01684 0.01006 -0.1406 0.4206 1.0000
7.500 1.4076 0.01724 0.01047 -0.1391 0.4038 1.0000
7.750 1.4258 0.01767 0.01090 -0.1374 0.3836 1.0000
8.000 1.4417 0.01818 0.01137 -0.1353 0.3579 1.0000
8.250 1.4541 0.01881 0.01190 -0.1328 0.3215 1.0000
8.500 1.4594 0.01973 0.01260 -0.1291 0.2874 1.0000
8.750 1.4637 0.02084 0.01351 -0.1255 0.2659 1.0000
9.000 1.4701 0.02199 0.01454 -0.1224 0.2504 1.0000
9.250 1.4772 0.02318 0.01564 -0.1196 0.2381 1.0000
9.500 1.4878 0.02422 0.01667 -0.1173 0.2269 1.0000
9.750 1.4971 0.02536 0.01781 -0.1150 0.2170 1.0000
10.000 1.5057 0.02658 0.01899 -0.1126 0.2073 1.0000
10.250 1.5171 0.02762 0.02010 -0.1107 0.1975 1.0000
10.500 1.5243 0.02897 0.02141 -0.1085 0.1885 1.0000
10.750 1.5360 0.02999 0.02255 -0.1068 0.1785 1.0000
11.000 1.5449 0.03127 0.02388 -0.1049 0.1700 1.0000
11.250 1.5538 0.03257 0.02522 -0.1032 0.1609 1.0000
11.500 1.5637 0.03384 0.02656 -0.1016 0.1517 1.0000
11.750 1.5699 0.03543 0.02814 -0.0999 0.1439 1.0000
12.000 1.5794 0.03681 0.02961 -0.0984 0.1353 1.0000
12.250 1.5856 0.03850 0.03134 -0.0969 0.1270 1.0000
12.500 1.5899 0.04041 0.03326 -0.0954 0.1189 1.0000
12.750 1.5948 0.04233 0.03523 -0.0940 0.1098 1.0000
13.000 1.5956 0.04470 0.03760 -0.0926 0.1000 1.0000
13.250 1.5930 0.04748 0.04038 -0.0912 0.0902 1.0000
13.500 1.5876 0.05068 0.04357 -0.0899 0.0801 1.0000
13.750 1.5851 0.05374 0.04667 -0.0888 0.0669 1.0000
14.250 1.5755 0.06066 0.05351 -0.0873 0.0447 1.0000
14.500 1.5690 0.06450 0.05738 -0.0868 0.0411 1.0000
14.750 1.5601 0.06874 0.06166 -0.0865 0.0389 1.0000
15.000 1.5533 0.07282 0.06585 -0.0863 0.0373 1.0000
15.250 1.5462 0.07703 0.07018 -0.0864 0.0360 1.0000
15.500 1.5381 0.08147 0.07472 -0.0866 0.0349 1.0000
15.750 1.5284 0.08619 0.07953 -0.0871 0.0341 1.0000
16.000 1.5172 0.09119 0.08461 -0.0877 0.0333 1.0000
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Polar data table (+)
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