GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 500 AIRFOIL (goe500-il) Reynolds number: 200,000 Max Cl/Cd: 91.74 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe500-il-200000-n5.txt Download as CSV file: xf-goe500-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 500 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2119 0.10115 0.09740 -0.0698 0.9762 0.0241
-9.750 -0.2017 0.09641 0.09265 -0.0741 0.9740 0.0246
-9.500 -0.1967 0.09196 0.08820 -0.0772 0.9689 0.0250
-9.000 -0.1759 0.08249 0.07872 -0.0868 0.9627 0.0273
-8.750 -0.1617 0.08002 0.07625 -0.0893 0.9584 0.0282
-8.500 -0.1513 0.07598 0.07220 -0.0933 0.9533 0.0289
-8.000 -0.1940 0.02973 0.02487 -0.1533 0.9217 0.0326
-7.750 -0.1649 0.02683 0.02165 -0.1573 0.9186 0.0340
-7.500 -0.1376 0.02555 0.02020 -0.1588 0.9149 0.0352
-7.250 -0.1141 0.02435 0.01878 -0.1594 0.9092 0.0368
-7.000 -0.0853 0.02268 0.01675 -0.1611 0.9055 0.0386
-6.750 -0.0546 0.02111 0.01479 -0.1627 0.9027 0.0400
-6.500 -0.0286 0.01991 0.01334 -0.1631 0.8981 0.0416
-6.250 -0.0031 0.01908 0.01240 -0.1632 0.8930 0.0430
-6.000 0.0260 0.01828 0.01147 -0.1638 0.8894 0.0444
-5.750 0.0568 0.01749 0.01051 -0.1646 0.8865 0.0459
-5.500 0.0814 0.01692 0.00979 -0.1642 0.8806 0.0476
-5.250 0.1092 0.01635 0.00906 -0.1642 0.8760 0.0496
-5.000 0.1391 0.01567 0.00827 -0.1647 0.8725 0.0515
-4.750 0.1662 0.01517 0.00773 -0.1647 0.8676 0.0536
-4.500 0.1929 0.01478 0.00727 -0.1645 0.8619 0.0562
-4.250 0.2225 0.01435 0.00675 -0.1648 0.8579 0.0595
-4.000 0.2500 0.01399 0.00637 -0.1647 0.8524 0.0640
-3.750 0.2773 0.01372 0.00606 -0.1645 0.8457 0.0711
-3.500 0.3071 0.01341 0.00574 -0.1647 0.8399 0.0802
-3.250 0.3331 0.01320 0.00550 -0.1642 0.8305 0.0899
-3.000 0.3617 0.01300 0.00519 -0.1641 0.8232 0.0999
-2.750 0.3889 0.01281 0.00498 -0.1639 0.8154 0.1091
-2.500 0.4176 0.01262 0.00473 -0.1639 0.8095 0.1181
-2.250 0.4446 0.01248 0.00458 -0.1637 0.8018 0.1275
-2.000 0.4737 0.01227 0.00436 -0.1638 0.7959 0.1379
-1.750 0.5005 0.01215 0.00423 -0.1636 0.7877 0.1487
-1.250 0.5565 0.01185 0.00397 -0.1635 0.7733 0.1737
-1.000 0.5855 0.01169 0.00382 -0.1635 0.7665 0.1940
-0.750 0.6123 0.01159 0.00381 -0.1633 0.7578 0.2265
-0.500 0.6408 0.01149 0.00374 -0.1633 0.7505 0.2619
-0.250 0.6678 0.01145 0.00375 -0.1631 0.7420 0.2922
0.000 0.6958 0.01141 0.00372 -0.1630 0.7347 0.3198
0.250 0.7227 0.01140 0.00375 -0.1627 0.7258 0.3459
0.500 0.7501 0.01138 0.00377 -0.1625 0.7176 0.3742
0.750 0.7769 0.01137 0.00382 -0.1622 0.7087 0.4070
1.000 0.8038 0.01138 0.00390 -0.1619 0.7001 0.4449
1.250 0.8305 0.01137 0.00399 -0.1616 0.6917 0.4922
1.500 0.8564 0.01137 0.00410 -0.1611 0.6828 0.5394
1.750 0.8824 0.01135 0.00419 -0.1606 0.6742 0.5954
2.000 0.9075 0.01130 0.00430 -0.1600 0.6642 0.6639
2.500 0.9605 0.01105 0.00441 -0.1590 0.6452 1.0000
2.750 0.9865 0.01121 0.00454 -0.1586 0.6355 1.0000
3.000 1.0127 0.01139 0.00466 -0.1582 0.6260 1.0000
3.250 1.0382 0.01158 0.00483 -0.1577 0.6153 1.0000
3.500 1.0636 0.01177 0.00500 -0.1572 0.6046 1.0000
3.750 1.0891 0.01198 0.00517 -0.1566 0.5946 1.0000
4.000 1.1141 0.01220 0.00537 -0.1560 0.5834 1.0000
4.250 1.1384 0.01242 0.00558 -0.1553 0.5709 1.0000
4.500 1.1623 0.01267 0.00580 -0.1545 0.5572 1.0000
4.750 1.1853 0.01294 0.00603 -0.1535 0.5414 1.0000
5.000 1.2075 0.01324 0.00628 -0.1524 0.5243 1.0000
5.250 1.2292 0.01356 0.00654 -0.1512 0.5071 1.0000
5.500 1.2506 0.01391 0.00684 -0.1500 0.4905 1.0000
5.750 1.2716 0.01428 0.00717 -0.1488 0.4745 1.0000
6.000 1.2916 0.01467 0.00752 -0.1473 0.4566 1.0000
6.250 1.3108 0.01510 0.00790 -0.1458 0.4375 1.0000
6.500 1.3280 0.01559 0.00833 -0.1439 0.4154 1.0000
6.750 1.3452 0.01608 0.00877 -0.1420 0.3952 1.0000
7.000 1.3622 0.01656 0.00924 -0.1402 0.3727 1.0000
7.250 1.3756 0.01713 0.00974 -0.1377 0.3432 1.0000
7.500 1.3833 0.01789 0.01034 -0.1343 0.3027 1.0000
7.750 1.3834 0.01910 0.01123 -0.1299 0.2504 1.0000
8.000 1.3842 0.02048 0.01235 -0.1260 0.2054 1.0000
8.250 1.3847 0.02201 0.01361 -0.1222 0.1568 1.0000
8.500 1.3837 0.02372 0.01504 -0.1185 0.1121 1.0000
8.750 1.3855 0.02535 0.01648 -0.1153 0.0801 1.0000
9.000 1.3902 0.02683 0.01786 -0.1126 0.0638 1.0000
9.250 1.3970 0.02821 0.01923 -0.1102 0.0558 1.0000
9.500 1.4055 0.02950 0.02058 -0.1081 0.0509 1.0000
9.750 1.4129 0.03090 0.02205 -0.1060 0.0470 1.0000
10.000 1.4175 0.03257 0.02377 -0.1037 0.0437 1.0000
10.250 1.4261 0.03396 0.02527 -0.1019 0.0412 1.0000
10.500 1.4329 0.03554 0.02695 -0.1001 0.0387 1.0000
10.750 1.4370 0.03741 0.02889 -0.0983 0.0365 1.0000
11.000 1.4384 0.03960 0.03115 -0.0964 0.0345 1.0000
11.250 1.4451 0.04136 0.03305 -0.0949 0.0327 1.0000
11.500 1.4500 0.04335 0.03517 -0.0935 0.0309 1.0000
11.750 1.4536 0.04553 0.03743 -0.0922 0.0293 1.0000
12.000 1.4535 0.04817 0.04012 -0.0908 0.0279 1.0000
12.250 1.4564 0.05059 0.04267 -0.0897 0.0265 1.0000
12.500 1.4610 0.05288 0.04509 -0.0888 0.0251 1.0000
12.750 1.4644 0.05538 0.04770 -0.0880 0.0238 1.0000
13.000 1.4672 0.05801 0.05042 -0.0873 0.0228 1.0000
13.250 1.4683 0.06091 0.05339 -0.0867 0.0218 1.0000
13.500 1.4691 0.06392 0.05650 -0.0861 0.0210 1.0000
13.750 1.4727 0.06665 0.05939 -0.0857 0.0200 1.0000
14.000 1.4758 0.06951 0.06238 -0.0854 0.0190 1.0000
14.250 1.4783 0.07248 0.06547 -0.0853 0.0182 1.0000
14.500 1.4801 0.07561 0.06869 -0.0853 0.0175 1.0000
14.750 1.4808 0.07894 0.07211 -0.0854 0.0170 1.0000
15.000 1.4801 0.08250 0.07575 -0.0855 0.0165 1.0000
15.250 1.4817 0.08582 0.07923 -0.0856 0.0161 1.0000
15.500 1.4830 0.08922 0.08280 -0.0858 0.0155 1.0000
15.750 1.4837 0.09275 0.08651 -0.0862 0.0150 1.0000
16.000 1.4839 0.09643 0.09033 -0.0868 0.0145 1.0000
16.250 1.4835 0.10025 0.09429 -0.0877 0.0140 1.0000
16.500 1.4826 0.10423 0.09839 -0.0888 0.0136 1.0000
16.750 1.4811 0.10834 0.10260 -0.0901 0.0133 1.0000
17.000 1.4790 0.11256 0.10693 -0.0915 0.0130 1.0000
17.250 1.4764 0.11687 0.11133 -0.0929 0.0127 1.0000
17.500 1.4730 0.12144 0.11609 -0.0945 0.0125 1.0000
17.750 1.4686 0.12633 0.12120 -0.0964 0.0122 1.0000
18.000 1.4630 0.13154 0.12662 -0.0987 0.0120 1.0000
18.250 1.4563 0.13706 0.13235 -0.1013 0.0118 1.0000
18.500 1.4482 0.14299 0.13850 -0.1045 0.0117 1.0000
18.750 1.4389 0.14931 0.14503 -0.1080 0.0115 1.0000
19.000 1.4281 0.15617 0.15210 -0.1122 0.0114 1.0000
19.250 1.4159 0.16364 0.15977 -0.1169 0.0113 1.0000
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