GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 501 AIRFOIL (goe501-il) Reynolds number: 200,000 Max Cl/Cd: 85.45 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe501-il-200000.txt Download as CSV file: xf-goe501-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 501 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2027 0.11710 0.11348 -0.0619 0.9826 0.0660
-10.250 -0.2026 0.11381 0.11020 -0.0685 0.9763 0.0704
-10.000 -0.2003 0.10828 0.10468 -0.0760 0.9723 0.0716
-9.750 -0.1710 0.10489 0.10126 -0.0758 0.9711 0.0728
-9.500 -0.1460 0.10180 0.09814 -0.0782 0.9697 0.0746
-9.250 -0.1350 0.09922 0.09557 -0.0797 0.9631 0.0776
-9.000 -0.1464 0.09361 0.08998 -0.0958 0.9560 0.0823
-8.750 -0.1141 0.09017 0.08650 -0.0928 0.9560 0.0838
-8.500 -0.0983 0.08820 0.08452 -0.0921 0.9498 0.0852
-8.250 -0.0780 0.08545 0.08175 -0.0946 0.9458 0.0883
-7.750 -0.0661 0.07790 0.07422 -0.1042 0.9323 0.0963
-7.500 -0.0362 0.07551 0.07179 -0.1059 0.9299 0.0991
-7.000 -0.0891 0.04529 0.04114 -0.1448 0.8996 0.0834
-6.750 -0.0638 0.03758 0.03299 -0.1533 0.8958 0.0794
-6.500 -0.0305 0.03035 0.02491 -0.1617 0.8935 0.0782
-6.250 -0.0191 0.02844 0.02265 -0.1605 0.8844 0.0792
-6.000 0.0160 0.02630 0.02002 -0.1630 0.8814 0.0811
-5.750 0.0537 0.02439 0.01767 -0.1655 0.8792 0.0825
-5.500 0.0897 0.02231 0.01544 -0.1676 0.8776 0.0848
-5.250 0.1053 0.02191 0.01500 -0.1657 0.8699 0.0869
-5.000 0.1368 0.02106 0.01402 -0.1664 0.8665 0.0898
-4.750 0.1718 0.02010 0.01287 -0.1676 0.8641 0.0924
-4.500 0.2078 0.01908 0.01168 -0.1690 0.8621 0.0953
-4.250 0.2297 0.01860 0.01125 -0.1681 0.8562 0.0986
-4.000 0.2577 0.01815 0.01077 -0.1680 0.8514 0.1025
-3.750 0.2918 0.01752 0.01003 -0.1688 0.8484 0.1065
-3.500 0.3271 0.01680 0.00937 -0.1700 0.8459 0.1125
-3.250 0.3504 0.01667 0.00921 -0.1691 0.8397 0.1184
-3.000 0.3794 0.01624 0.00883 -0.1691 0.8347 0.1254
-2.750 0.4137 0.01577 0.00834 -0.1699 0.8312 0.1373
-2.500 0.4490 0.01523 0.00785 -0.1710 0.8282 0.1578
-2.250 0.4697 0.01506 0.00782 -0.1697 0.8201 0.1887
-2.000 0.5021 0.01470 0.00754 -0.1703 0.8155 0.2264
-1.750 0.5371 0.01441 0.00724 -0.1713 0.8118 0.2545
-1.500 0.5589 0.01446 0.00735 -0.1700 0.8033 0.2735
-1.250 0.5912 0.01426 0.00715 -0.1705 0.7982 0.2966
-1.000 0.6193 0.01420 0.00709 -0.1702 0.7914 0.3197
-0.750 0.6471 0.01408 0.00699 -0.1699 0.7839 0.3413
-0.500 0.6804 0.01388 0.00678 -0.1705 0.7784 0.3649
-0.250 0.7037 0.01387 0.00681 -0.1694 0.7685 0.3876
0.000 0.7353 0.01364 0.00658 -0.1697 0.7610 0.4127
0.250 0.7601 0.01352 0.00651 -0.1687 0.7499 0.4345
0.500 0.7872 0.01339 0.00640 -0.1682 0.7398 0.4587
0.750 0.8158 0.01322 0.00626 -0.1680 0.7301 0.4832
1.000 0.8402 0.01316 0.00628 -0.1671 0.7184 0.5072
1.250 0.8674 0.01306 0.00622 -0.1666 0.7078 0.5344
1.500 0.8939 0.01296 0.00616 -0.1660 0.6963 0.5673
1.750 0.9174 0.01288 0.00620 -0.1649 0.6832 0.6076
2.000 0.9409 0.01272 0.00620 -0.1638 0.6704 0.6679
2.250 0.9653 0.01210 0.00605 -0.1625 0.6579 1.0000
2.500 0.9921 0.01220 0.00598 -0.1621 0.6451 1.0000
2.750 1.0167 0.01233 0.00603 -0.1613 0.6309 1.0000
3.000 1.0415 0.01249 0.00610 -0.1607 0.6176 1.0000
3.250 1.0667 0.01268 0.00618 -0.1600 0.6055 1.0000
3.500 1.0925 0.01288 0.00626 -0.1595 0.5945 1.0000
3.750 1.1175 0.01312 0.00641 -0.1589 0.5833 1.0000
4.000 1.1421 0.01338 0.00660 -0.1583 0.5727 1.0000
4.250 1.1681 0.01367 0.00677 -0.1578 0.5632 1.0000
4.500 1.1921 0.01397 0.00703 -0.1571 0.5531 1.0000
4.750 1.2176 0.01430 0.00728 -0.1566 0.5445 1.0000
5.000 1.2422 0.01462 0.00758 -0.1561 0.5363 1.0000
5.250 1.2687 0.01499 0.00787 -0.1558 0.5293 1.0000
5.500 1.2920 0.01531 0.00822 -0.1550 0.5214 1.0000
6.000 1.3415 0.01602 0.00892 -0.1540 0.5073 1.0000
6.250 1.3662 0.01638 0.00924 -0.1534 0.4999 1.0000
6.500 1.3880 0.01672 0.00962 -0.1523 0.4916 1.0000
6.750 1.4103 0.01705 0.00994 -0.1513 0.4827 1.0000
7.000 1.4292 0.01736 0.01030 -0.1497 0.4732 1.0000
7.250 1.4509 0.01770 0.01059 -0.1486 0.4641 1.0000
7.500 1.4678 0.01799 0.01101 -0.1467 0.4554 1.0000
7.750 1.4887 0.01834 0.01132 -0.1454 0.4472 1.0000
8.000 1.5031 0.01864 0.01175 -0.1431 0.4377 1.0000
8.250 1.5190 0.01898 0.01208 -0.1410 0.4282 1.0000
8.500 1.5296 0.01930 0.01250 -0.1379 0.4180 1.0000
8.750 1.5411 0.01970 0.01294 -0.1350 0.4076 1.0000
9.000 1.5517 0.02015 0.01338 -0.1321 0.3966 1.0000
9.250 1.5599 0.02064 0.01396 -0.1290 0.3836 1.0000
9.500 1.5669 0.02125 0.01461 -0.1257 0.3688 1.0000
9.750 1.5723 0.02199 0.01536 -0.1224 0.3516 1.0000
10.000 1.5760 0.02290 0.01624 -0.1190 0.3327 1.0000
10.250 1.5789 0.02397 0.01729 -0.1157 0.3094 1.0000
10.500 1.5779 0.02537 0.01858 -0.1122 0.2854 1.0000
10.750 1.5778 0.02690 0.02002 -0.1090 0.2620 1.0000
11.000 1.5771 0.02861 0.02164 -0.1060 0.2435 1.0000
11.250 1.5778 0.03035 0.02332 -0.1034 0.2290 1.0000
11.500 1.5793 0.03214 0.02508 -0.1010 0.2171 1.0000
11.750 1.5803 0.03405 0.02695 -0.0988 0.2067 1.0000
12.000 1.5802 0.03613 0.02898 -0.0966 0.1968 1.0000
12.250 1.5825 0.03810 0.03098 -0.0948 0.1870 1.0000
12.500 1.5815 0.04042 0.03328 -0.0929 0.1777 1.0000
12.750 1.5815 0.04275 0.03563 -0.0912 0.1678 1.0000
13.000 1.5828 0.04505 0.03800 -0.0898 0.1578 1.0000
13.250 1.5801 0.04780 0.04071 -0.0884 0.1485 1.0000
13.500 1.5819 0.05024 0.04328 -0.0874 0.1376 1.0000
13.750 1.5834 0.05281 0.04593 -0.0865 0.1267 1.0000
14.000 1.5834 0.05561 0.04878 -0.0857 0.1169 1.0000
14.500 1.5814 0.06174 0.05495 -0.0847 0.1009 1.0000
14.750 1.5775 0.06530 0.05850 -0.0843 0.0954 1.0000
15.000 1.5757 0.06867 0.06193 -0.0840 0.0903 1.0000
15.250 1.5692 0.07272 0.06595 -0.0840 0.0861 1.0000
15.500 1.5684 0.07611 0.06944 -0.0839 0.0820 1.0000
15.750 1.5652 0.07988 0.07327 -0.0841 0.0781 1.0000
16.000 1.5602 0.08382 0.07717 -0.0842 0.0743 1.0000
16.250 1.5599 0.08737 0.08089 -0.0845 0.0704 1.0000
16.500 1.5566 0.09125 0.08480 -0.0850 0.0667 1.0000
16.750 1.5545 0.09497 0.08857 -0.0854 0.0627 1.0000
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