GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 501 AIRFOIL (goe501-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.87 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe501-il-1000000-n5.txt Download as CSV file: xf-goe501-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.5405 0.08512 0.08289 -0.0973 0.9798 0.0206
-15.000 -0.6136 0.06749 0.06503 -0.1125 0.9753 0.0208
-14.750 -0.6666 0.05155 0.04885 -0.1317 0.9709 0.0205
-14.500 -0.7154 0.03706 0.03407 -0.1509 0.9560 0.0206
-14.250 -0.7574 0.02564 0.02231 -0.1647 0.9376 0.0204
-14.000 -0.7439 0.02219 0.01864 -0.1696 0.9306 0.0210
-13.750 -0.7257 0.02076 0.01708 -0.1707 0.9258 0.0215
-13.500 -0.7060 0.01960 0.01584 -0.1713 0.9203 0.0221
-13.250 -0.6839 0.01874 0.01489 -0.1717 0.9152 0.0228
-13.000 -0.6609 0.01798 0.01405 -0.1720 0.9103 0.0235
-12.750 -0.6373 0.01731 0.01330 -0.1721 0.9041 0.0241
-12.500 -0.6129 0.01673 0.01261 -0.1722 0.8980 0.0247
-12.250 -0.5884 0.01612 0.01191 -0.1724 0.8915 0.0253
-12.000 -0.5635 0.01555 0.01128 -0.1724 0.8842 0.0261
-11.750 -0.5380 0.01507 0.01073 -0.1725 0.8773 0.0267
-11.500 -0.5122 0.01464 0.01022 -0.1725 0.8691 0.0274
-11.250 -0.4862 0.01423 0.00972 -0.1725 0.8614 0.0280
-11.000 -0.4599 0.01388 0.00927 -0.1725 0.8527 0.0287
-10.750 -0.4334 0.01354 0.00884 -0.1724 0.8446 0.0291
-10.500 -0.4074 0.01311 0.00833 -0.1724 0.8360 0.0299
-10.250 -0.3806 0.01279 0.00794 -0.1724 0.8283 0.0307
-10.000 -0.3538 0.01250 0.00759 -0.1724 0.8203 0.0314
-9.750 -0.3268 0.01225 0.00726 -0.1724 0.8122 0.0321
-9.500 -0.2999 0.01202 0.00693 -0.1722 0.8028 0.0329
-9.250 -0.2727 0.01179 0.00662 -0.1722 0.7939 0.0335
-9.000 -0.2457 0.01158 0.00631 -0.1721 0.7851 0.0339
-8.750 -0.2185 0.01124 0.00592 -0.1721 0.7782 0.0348
-8.500 -0.1909 0.01101 0.00563 -0.1721 0.7720 0.0356
-8.000 -0.1353 0.01059 0.00512 -0.1721 0.7620 0.0371
-7.750 -0.1073 0.01040 0.00487 -0.1721 0.7568 0.0378
-7.500 -0.0794 0.01023 0.00463 -0.1721 0.7517 0.0385
-7.250 -0.0513 0.01008 0.00442 -0.1721 0.7475 0.0391
-7.000 -0.0230 0.00984 0.00415 -0.1722 0.7436 0.0401
-6.750 0.0052 0.00965 0.00394 -0.1722 0.7396 0.0411
-6.500 0.0333 0.00951 0.00376 -0.1722 0.7350 0.0420
-6.250 0.0615 0.00938 0.00359 -0.1722 0.7305 0.0430
-6.000 0.0900 0.00924 0.00341 -0.1723 0.7267 0.0440
-5.750 0.1186 0.00912 0.00326 -0.1723 0.7231 0.0448
-5.500 0.1468 0.00901 0.00310 -0.1723 0.7187 0.0457
-5.250 0.1749 0.00888 0.00293 -0.1723 0.7140 0.0473
-5.000 0.2036 0.00875 0.00281 -0.1723 0.7101 0.0487
-4.750 0.2321 0.00865 0.00269 -0.1724 0.7060 0.0500
-4.500 0.2605 0.00857 0.00257 -0.1724 0.7016 0.0512
-4.000 0.3174 0.00839 0.00234 -0.1724 0.6937 0.0537
-3.750 0.3459 0.00829 0.00224 -0.1724 0.6889 0.0556
-3.500 0.3737 0.00825 0.00217 -0.1723 0.6816 0.0575
-3.250 0.4019 0.00819 0.00208 -0.1722 0.6735 0.0592
-3.000 0.4294 0.00817 0.00201 -0.1720 0.6640 0.0604
-2.750 0.4575 0.00811 0.00193 -0.1720 0.6543 0.0624
-2.500 0.4849 0.00808 0.00186 -0.1718 0.6418 0.0651
-2.250 0.5119 0.00808 0.00180 -0.1715 0.6256 0.0675
-2.000 0.5373 0.00818 0.00178 -0.1709 0.5978 0.0694
-1.750 0.5616 0.00836 0.00179 -0.1701 0.5656 0.0715
-1.500 0.5870 0.00846 0.00180 -0.1696 0.5433 0.0758
-1.250 0.6129 0.00856 0.00182 -0.1692 0.5272 0.0799
-1.000 0.6391 0.00862 0.00185 -0.1688 0.5142 0.0881
-0.750 0.6657 0.00857 0.00188 -0.1686 0.5035 0.1305
-0.500 0.6925 0.00862 0.00193 -0.1683 0.4947 0.1448
-0.250 0.7194 0.00867 0.00197 -0.1680 0.4867 0.1524
0.000 0.7460 0.00874 0.00202 -0.1677 0.4790 0.1598
0.250 0.7727 0.00881 0.00207 -0.1675 0.4700 0.1656
0.500 0.7989 0.00889 0.00213 -0.1671 0.4605 0.1756
0.750 0.8252 0.00895 0.00220 -0.1667 0.4509 0.1896
1.000 0.8517 0.00899 0.00227 -0.1665 0.4445 0.2120
1.250 0.8784 0.00900 0.00235 -0.1662 0.4383 0.2462
1.500 0.9044 0.00906 0.00245 -0.1659 0.4316 0.2733
1.750 0.9309 0.00911 0.00254 -0.1656 0.4260 0.2943
2.000 0.9570 0.00919 0.00264 -0.1652 0.4192 0.3088
2.250 0.9824 0.00931 0.00275 -0.1647 0.4120 0.3246
2.500 1.0084 0.00939 0.00285 -0.1643 0.4053 0.3383
2.750 1.0335 0.00952 0.00298 -0.1637 0.3978 0.3530
3.000 1.0591 0.00961 0.00309 -0.1633 0.3919 0.3667
3.250 1.0841 0.00973 0.00322 -0.1627 0.3846 0.3774
3.500 1.1087 0.00987 0.00335 -0.1621 0.3776 0.3889
3.750 1.1334 0.00999 0.00349 -0.1615 0.3702 0.4035
4.000 1.1569 0.01016 0.00365 -0.1606 0.3609 0.4182
4.250 1.1795 0.01036 0.00384 -0.1597 0.3482 0.4348
4.500 1.2004 0.01061 0.00407 -0.1584 0.3307 0.4632
4.750 1.2186 0.01091 0.00437 -0.1567 0.3057 0.5168
5.000 1.2340 0.01128 0.00470 -0.1544 0.2808 0.5663
5.250 1.2388 0.01215 0.00531 -0.1503 0.2229 0.6020
5.500 1.2468 0.01292 0.00594 -0.1469 0.1816 0.6418
5.750 1.2643 0.01312 0.00632 -0.1451 0.1728 0.7376
6.250 1.3038 0.01336 0.00693 -0.1423 0.1628 1.0000
6.500 1.3242 0.01364 0.00721 -0.1410 0.1608 1.0000
6.750 1.3443 0.01393 0.00751 -0.1398 0.1589 1.0000
7.000 1.3637 0.01427 0.00784 -0.1384 0.1562 1.0000
7.250 1.3822 0.01465 0.00821 -0.1369 0.1527 1.0000
7.500 1.4011 0.01501 0.00858 -0.1355 0.1499 1.0000
7.750 1.4204 0.01536 0.00894 -0.1342 0.1479 1.0000
8.000 1.4402 0.01568 0.00929 -0.1330 0.1469 1.0000
8.250 1.4597 0.01602 0.00966 -0.1318 0.1454 1.0000
8.500 1.4786 0.01640 0.01006 -0.1305 0.1433 1.0000
8.750 1.4965 0.01683 0.01050 -0.1291 0.1404 1.0000
9.000 1.5135 0.01732 0.01099 -0.1276 0.1369 1.0000
9.250 1.5300 0.01785 0.01152 -0.1260 0.1325 1.0000
9.500 1.5469 0.01836 0.01203 -0.1246 0.1260 1.0000
10.000 1.5594 0.02068 0.01404 -0.1192 0.0812 1.0000
10.250 1.5674 0.02179 0.01512 -0.1168 0.0715 1.0000
10.500 1.5788 0.02272 0.01606 -0.1150 0.0671 1.0000
10.750 1.5901 0.02369 0.01703 -0.1132 0.0631 1.0000
11.000 1.6025 0.02460 0.01797 -0.1116 0.0606 1.0000
11.250 1.6132 0.02566 0.01904 -0.1099 0.0576 1.0000
11.500 1.6237 0.02676 0.02016 -0.1082 0.0550 1.0000
11.750 1.6357 0.02779 0.02122 -0.1068 0.0534 1.0000
12.000 1.6468 0.02890 0.02237 -0.1053 0.0512 1.0000
12.250 1.6561 0.03018 0.02367 -0.1038 0.0489 1.0000
12.500 1.6646 0.03157 0.02508 -0.1023 0.0465 1.0000
12.750 1.6754 0.03280 0.02635 -0.1010 0.0450 1.0000
13.000 1.6847 0.03420 0.02779 -0.0998 0.0429 1.0000
13.250 1.6926 0.03576 0.02938 -0.0984 0.0407 1.0000
13.500 1.7000 0.03739 0.03103 -0.0972 0.0385 1.0000
13.750 1.7075 0.03906 0.03274 -0.0960 0.0361 1.0000
14.000 1.7124 0.04101 0.03470 -0.0948 0.0328 1.0000
14.250 1.7165 0.04311 0.03681 -0.0937 0.0287 1.0000
14.500 1.7165 0.04567 0.03938 -0.0924 0.0233 1.0000
14.750 1.7155 0.04844 0.04215 -0.0914 0.0190 1.0000
15.000 1.7161 0.05113 0.04488 -0.0905 0.0167 1.0000
15.250 1.7185 0.05369 0.04749 -0.0898 0.0154 1.0000
15.500 1.7194 0.05649 0.05035 -0.0891 0.0143 1.0000
15.750 1.7208 0.05931 0.05324 -0.0887 0.0135 1.0000
16.000 1.7227 0.06215 0.05615 -0.0884 0.0128 1.0000
16.250 1.7240 0.06515 0.05922 -0.0882 0.0122 1.0000
16.500 1.7240 0.06839 0.06253 -0.0881 0.0117 1.0000
16.750 1.7234 0.07176 0.06597 -0.0882 0.0112 1.0000
17.000 1.7239 0.07506 0.06935 -0.0884 0.0108 1.0000
17.250 1.7240 0.07848 0.07285 -0.0887 0.0104 1.0000
17.500 1.7232 0.08208 0.07653 -0.0892 0.0100 1.0000
17.750 1.7216 0.08584 0.08036 -0.0897 0.0097 1.0000
18.000 1.7196 0.08968 0.08429 -0.0904 0.0094 1.0000
18.250 1.7170 0.09367 0.08836 -0.0912 0.0091 1.0000
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Polar data table (+)
Polar graphs
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