GOE 498 AIRFOIL (goe498-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 498 AIRFOIL (goe498-il) Reynolds number: 200,000 Max Cl/Cd: 73.49 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe498-il-200000-n5.txt Download as CSV file: xf-goe498-il-200000-n5.csv |
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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6194 0.06361 0.05882 -0.0923 0.9926 0.0476
-13.000 -0.6638 0.05102 0.04581 -0.1066 0.9842 0.0480
-12.750 -0.6782 0.04392 0.03839 -0.1159 0.9754 0.0484
-12.500 -0.6683 0.04024 0.03458 -0.1218 0.9695 0.0489
-12.250 -0.6633 0.03761 0.03187 -0.1250 0.9603 0.0493
-12.000 -0.6406 0.03515 0.02930 -0.1299 0.9557 0.0500
-11.750 -0.6273 0.03340 0.02743 -0.1313 0.9477 0.0506
-11.500 -0.6044 0.03163 0.02549 -0.1338 0.9430 0.0516
-11.250 -0.5770 0.02984 0.02347 -0.1369 0.9401 0.0529
-11.000 -0.5624 0.02845 0.02185 -0.1367 0.9319 0.0540
-10.750 -0.5335 0.02748 0.02089 -0.1382 0.9278 0.0549
-10.500 -0.5010 0.02647 0.01982 -0.1404 0.9249 0.0559
-10.250 -0.4743 0.02553 0.01877 -0.1412 0.9200 0.0571
-10.000 -0.4516 0.02461 0.01771 -0.1413 0.9129 0.0585
-9.750 -0.4209 0.02363 0.01657 -0.1427 0.9085 0.0600
-9.500 -0.3865 0.02285 0.01578 -0.1446 0.9052 0.0614
-9.250 -0.3663 0.02228 0.01516 -0.1436 0.8963 0.0629
-9.000 -0.3368 0.02155 0.01431 -0.1444 0.8904 0.0648
-8.750 -0.3031 0.02077 0.01339 -0.1460 0.8862 0.0666
-8.500 -0.2827 0.02025 0.01288 -0.1449 0.8767 0.0680
-8.250 -0.2536 0.01967 0.01224 -0.1454 0.8702 0.0701
-8.000 -0.2233 0.01911 0.01155 -0.1460 0.8641 0.0725
-7.750 -0.2009 0.01859 0.01101 -0.1452 0.8545 0.0743
-7.500 -0.1706 0.01803 0.01042 -0.1459 0.8481 0.0766
-7.250 -0.1466 0.01761 0.00994 -0.1452 0.8388 0.0789
-7.000 -0.1181 0.01715 0.00938 -0.1454 0.8308 0.0816
-6.750 -0.0921 0.01666 0.00890 -0.1452 0.8222 0.0841
-6.500 -0.0650 0.01627 0.00844 -0.1451 0.8135 0.0872
-6.250 -0.0369 0.01588 0.00799 -0.1451 0.8054 0.0903
-6.000 -0.0104 0.01549 0.00758 -0.1449 0.7960 0.0938
-5.750 0.0183 0.01516 0.00718 -0.1450 0.7880 0.0980
-5.500 0.0450 0.01485 0.00687 -0.1447 0.7791 0.1025
-5.000 0.1009 0.01433 0.00630 -0.1446 0.7627 0.1159
-4.750 0.1296 0.01411 0.00605 -0.1446 0.7548 0.1258
-4.500 0.1569 0.01393 0.00586 -0.1444 0.7469 0.1381
-4.250 0.1846 0.01377 0.00567 -0.1442 0.7393 0.1512
-4.000 0.2133 0.01363 0.00547 -0.1442 0.7323 0.1640
-3.500 0.2676 0.01340 0.00521 -0.1437 0.7170 0.1886
-3.250 0.2952 0.01332 0.00512 -0.1435 0.7103 0.2008
-3.000 0.3218 0.01326 0.00506 -0.1431 0.7026 0.2133
-2.750 0.3499 0.01322 0.00498 -0.1429 0.6955 0.2270
-2.500 0.3765 0.01318 0.00496 -0.1425 0.6882 0.2410
-2.250 0.4029 0.01316 0.00494 -0.1420 0.6792 0.2558
-2.000 0.4299 0.01316 0.00489 -0.1416 0.6704 0.2692
-1.750 0.4555 0.01316 0.00487 -0.1410 0.6607 0.2828
-1.500 0.4827 0.01316 0.00485 -0.1406 0.6530 0.2971
-1.250 0.5084 0.01316 0.00488 -0.1400 0.6450 0.3100
-1.000 0.5349 0.01318 0.00487 -0.1395 0.6374 0.3225
-0.750 0.5615 0.01319 0.00489 -0.1391 0.6306 0.3352
-0.500 0.5874 0.01322 0.00492 -0.1385 0.6230 0.3483
-0.250 0.6136 0.01324 0.00495 -0.1380 0.6157 0.3613
0.000 0.6393 0.01327 0.00499 -0.1374 0.6075 0.3733
0.250 0.6645 0.01331 0.00501 -0.1367 0.5985 0.3857
0.500 0.6897 0.01334 0.00505 -0.1360 0.5896 0.3974
0.750 0.7146 0.01340 0.00510 -0.1352 0.5802 0.4102
1.000 0.7397 0.01345 0.00516 -0.1345 0.5720 0.4229
1.250 0.7645 0.01352 0.00525 -0.1337 0.5634 0.4368
1.500 0.7894 0.01361 0.00532 -0.1330 0.5557 0.4538
1.750 0.8137 0.01367 0.00546 -0.1322 0.5473 0.4743
2.000 0.8380 0.01377 0.00559 -0.1313 0.5393 0.4974
2.500 0.8853 0.01397 0.00587 -0.1294 0.5222 0.5433
2.750 0.9087 0.01409 0.00602 -0.1284 0.5138 0.5655
3.000 0.9319 0.01421 0.00618 -0.1274 0.5053 0.5860
3.250 0.9552 0.01435 0.00632 -0.1264 0.4979 0.6059
3.500 0.9777 0.01444 0.00651 -0.1253 0.4897 0.6278
3.750 0.9990 0.01457 0.00667 -0.1239 0.4816 0.6534
4.000 1.0202 0.01465 0.00686 -0.1225 0.4730 0.6853
4.250 1.0406 0.01472 0.00705 -0.1209 0.4640 0.7359
4.500 1.0685 0.01458 0.00722 -0.1207 0.4546 1.0000
4.750 1.0890 0.01484 0.00742 -0.1194 0.4455 1.0000
5.000 1.1089 0.01509 0.00764 -0.1178 0.4367 1.0000
5.250 1.1276 0.01537 0.00787 -0.1161 0.4278 1.0000
5.500 1.1470 0.01566 0.00812 -0.1146 0.4200 1.0000
5.750 1.1655 0.01596 0.00840 -0.1129 0.4114 1.0000
6.000 1.1835 0.01630 0.00869 -0.1111 0.4032 1.0000
6.250 1.2015 0.01664 0.00901 -0.1094 0.3946 1.0000
6.500 1.2185 0.01702 0.00935 -0.1076 0.3866 1.0000
6.750 1.2359 0.01740 0.00972 -0.1058 0.3778 1.0000
7.000 1.2516 0.01785 0.01011 -0.1039 0.3701 1.0000
7.250 1.2696 0.01824 0.01053 -0.1023 0.3627 1.0000
7.500 1.2854 0.01871 0.01098 -0.1005 0.3554 1.0000
7.750 1.3020 0.01917 0.01144 -0.0988 0.3487 1.0000
8.000 1.3178 0.01967 0.01195 -0.0970 0.3412 1.0000
8.250 1.3313 0.02026 0.01251 -0.0950 0.3338 1.0000
8.500 1.3461 0.02082 0.01309 -0.0932 0.3248 1.0000
8.750 1.3570 0.02154 0.01377 -0.0909 0.3160 1.0000
9.000 1.3707 0.02218 0.01444 -0.0891 0.3062 1.0000
9.250 1.3805 0.02301 0.01524 -0.0869 0.2966 1.0000
9.500 1.3920 0.02380 0.01605 -0.0849 0.2858 1.0000
9.750 1.4013 0.02472 0.01696 -0.0828 0.2743 1.0000
10.000 1.4086 0.02579 0.01800 -0.0806 0.2619 1.0000
10.250 1.4148 0.02697 0.01915 -0.0785 0.2480 1.0000
10.500 1.4203 0.02826 0.02041 -0.0764 0.2333 1.0000
10.750 1.4243 0.02971 0.02182 -0.0743 0.2191 1.0000
11.000 1.4281 0.03126 0.02333 -0.0723 0.2070 1.0000
11.250 1.4313 0.03293 0.02498 -0.0705 0.1974 1.0000
11.500 1.4334 0.03475 0.02678 -0.0688 0.1897 1.0000
11.750 1.4384 0.03645 0.02849 -0.0674 0.1835 1.0000
12.000 1.4417 0.03833 0.03037 -0.0660 0.1781 1.0000
12.250 1.4452 0.04027 0.03233 -0.0647 0.1736 1.0000
12.500 1.4518 0.04201 0.03413 -0.0637 0.1694 1.0000
12.750 1.4560 0.04399 0.03615 -0.0627 0.1651 1.0000
13.000 1.4579 0.04624 0.03841 -0.0617 0.1611 1.0000
13.250 1.4642 0.04814 0.04038 -0.0609 0.1574 1.0000
13.500 1.4705 0.05008 0.04240 -0.0603 0.1533 1.0000
13.750 1.4735 0.05238 0.04475 -0.0596 0.1492 1.0000
14.000 1.4742 0.05498 0.04736 -0.0590 0.1454 1.0000
14.250 1.4825 0.05686 0.04938 -0.0587 0.1409 1.0000
14.500 1.4856 0.05935 0.05194 -0.0584 0.1356 1.0000
14.750 1.4874 0.06201 0.05467 -0.0581 0.1305 1.0000
15.000 1.4920 0.06445 0.05721 -0.0580 0.1236 1.0000
15.250 1.4935 0.06730 0.06013 -0.0580 0.1157 1.0000
15.500 1.4920 0.07059 0.06345 -0.0582 0.1048 1.0000
15.750 1.4856 0.07457 0.06740 -0.0585 0.0944 1.0000
16.000 1.4775 0.07887 0.07168 -0.0591 0.0874 1.0000
16.250 1.4691 0.08332 0.07614 -0.0598 0.0825 1.0000
16.500 1.4630 0.08752 0.08040 -0.0606 0.0787 1.0000
16.750 1.4557 0.09196 0.08488 -0.0615 0.0756 1.0000
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Polar data table (+)
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