GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 500 AIRFOIL (goe500-il) Reynolds number: 1,000,000 Max Cl/Cd: 159.15 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe500-il-1000000.txt Download as CSV file: xf-goe500-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2586 0.12614 0.12440 -0.0575 0.9916 0.0158
-12.000 -0.2548 0.11986 0.11811 -0.0623 0.9893 0.0174
-11.750 -0.5566 0.02424 0.02146 -0.1581 0.9534 0.0156
-11.500 -0.5350 0.02260 0.01969 -0.1599 0.9480 0.0160
-11.250 -0.5120 0.02121 0.01814 -0.1614 0.9437 0.0165
-11.000 -0.4880 0.02003 0.01679 -0.1625 0.9397 0.0170
-10.750 -0.4637 0.01931 0.01595 -0.1629 0.9360 0.0174
-10.500 -0.4425 0.01757 0.01401 -0.1639 0.9317 0.0182
-10.250 -0.4164 0.01716 0.01357 -0.1641 0.9285 0.0188
-10.000 -0.3897 0.01677 0.01311 -0.1644 0.9253 0.0194
-9.750 -0.3638 0.01629 0.01256 -0.1645 0.9223 0.0201
-9.500 -0.3378 0.01578 0.01195 -0.1647 0.9189 0.0208
-9.250 -0.3111 0.01537 0.01143 -0.1648 0.9157 0.0214
-9.000 -0.2863 0.01425 0.01013 -0.1651 0.9123 0.0222
-8.750 -0.2596 0.01376 0.00959 -0.1653 0.9091 0.0230
-8.500 -0.2326 0.01350 0.00930 -0.1654 0.9061 0.0238
-8.250 -0.2054 0.01321 0.00896 -0.1654 0.9027 0.0247
-8.000 -0.1782 0.01285 0.00851 -0.1654 0.8994 0.0255
-7.750 -0.1507 0.01256 0.00813 -0.1654 0.8963 0.0261
-7.500 -0.1241 0.01178 0.00721 -0.1656 0.8928 0.0270
-7.250 -0.0973 0.01125 0.00664 -0.1657 0.8893 0.0282
-7.000 -0.0698 0.01095 0.00631 -0.1657 0.8856 0.0291
-6.750 -0.0422 0.01062 0.00591 -0.1657 0.8821 0.0300
-6.500 -0.0142 0.01037 0.00557 -0.1657 0.8782 0.0309
-6.250 0.0133 0.01014 0.00530 -0.1656 0.8737 0.0317
-6.000 0.0409 0.00983 0.00493 -0.1655 0.8686 0.0323
-5.750 0.0682 0.00917 0.00415 -0.1655 0.8637 0.0338
-5.500 0.0958 0.00888 0.00384 -0.1655 0.8585 0.0351
-5.250 0.1236 0.00864 0.00355 -0.1654 0.8528 0.0363
-5.000 0.1516 0.00843 0.00327 -0.1654 0.8473 0.0374
-4.750 0.1794 0.00822 0.00302 -0.1653 0.8407 0.0384
-4.500 0.2074 0.00801 0.00274 -0.1652 0.8344 0.0396
-4.250 0.2354 0.00771 0.00241 -0.1652 0.8283 0.0425
-4.000 0.2634 0.00754 0.00220 -0.1651 0.8217 0.0448
-3.750 0.2915 0.00741 0.00202 -0.1651 0.8153 0.0470
-3.500 0.3195 0.00719 0.00180 -0.1650 0.8074 0.0541
-3.250 0.3473 0.00701 0.00166 -0.1649 0.7997 0.0700
-3.000 0.3751 0.00693 0.00163 -0.1648 0.7910 0.0883
-2.750 0.4030 0.00691 0.00157 -0.1647 0.7828 0.0954
-2.500 0.4307 0.00688 0.00152 -0.1646 0.7739 0.1021
-2.250 0.4586 0.00688 0.00148 -0.1645 0.7652 0.1061
-2.000 0.4861 0.00687 0.00141 -0.1643 0.7564 0.1102
-1.750 0.5138 0.00682 0.00135 -0.1642 0.7472 0.1157
-1.500 0.5413 0.00682 0.00132 -0.1640 0.7383 0.1201
-1.250 0.5688 0.00684 0.00128 -0.1638 0.7294 0.1227
-1.000 0.5965 0.00679 0.00124 -0.1637 0.7213 0.1301
-0.750 0.6238 0.00679 0.00123 -0.1635 0.7130 0.1393
-0.500 0.6515 0.00673 0.00121 -0.1634 0.7051 0.1582
-0.250 0.6786 0.00662 0.00124 -0.1633 0.6970 0.2174
0.000 0.7062 0.00656 0.00128 -0.1632 0.6890 0.2621
0.250 0.7332 0.00658 0.00132 -0.1630 0.6805 0.2899
0.500 0.7607 0.00658 0.00135 -0.1629 0.6719 0.3125
0.750 0.7877 0.00661 0.00140 -0.1627 0.6636 0.3352
1.000 0.8150 0.00662 0.00145 -0.1625 0.6550 0.3594
1.250 0.8420 0.00664 0.00152 -0.1623 0.6465 0.3879
1.750 0.8957 0.00666 0.00169 -0.1618 0.6278 0.4684
2.000 0.9219 0.00669 0.00179 -0.1615 0.6164 0.5196
2.250 0.9477 0.00674 0.00190 -0.1610 0.6035 0.5651
2.500 0.9737 0.00678 0.00201 -0.1606 0.5904 0.6136
2.750 0.9989 0.00679 0.00213 -0.1601 0.5754 0.6813
3.000 1.0233 0.00643 0.00227 -0.1594 0.5572 1.0000
3.250 1.0486 0.00662 0.00238 -0.1588 0.5393 1.0000
3.500 1.0733 0.00685 0.00251 -0.1582 0.5179 1.0000
3.750 1.0971 0.00713 0.00267 -0.1574 0.4957 1.0000
4.000 1.1219 0.00735 0.00282 -0.1568 0.4794 1.0000
4.250 1.1466 0.00758 0.00299 -0.1562 0.4652 1.0000
4.500 1.1709 0.00783 0.00317 -0.1555 0.4492 1.0000
4.750 1.1949 0.00809 0.00336 -0.1548 0.4319 1.0000
5.000 1.2191 0.00834 0.00355 -0.1541 0.4190 1.0000
5.250 1.2434 0.00857 0.00374 -0.1535 0.4052 1.0000
5.500 1.2668 0.00885 0.00395 -0.1527 0.3884 1.0000
5.750 1.2901 0.00914 0.00417 -0.1518 0.3675 1.0000
6.000 1.3100 0.00963 0.00448 -0.1505 0.3297 1.0000
6.250 1.3223 0.01061 0.00505 -0.1478 0.2573 1.0000
6.500 1.3331 0.01168 0.00575 -0.1450 0.1950 1.0000
6.750 1.3406 0.01291 0.00655 -0.1416 0.1233 1.0000
7.000 1.3464 0.01406 0.00736 -0.1379 0.0669 1.0000
7.250 1.3576 0.01479 0.00796 -0.1350 0.0466 1.0000
7.500 1.3735 0.01528 0.00843 -0.1329 0.0406 1.0000
7.750 1.3897 0.01575 0.00891 -0.1309 0.0374 1.0000
8.000 1.4038 0.01635 0.00951 -0.1286 0.0338 1.0000
8.250 1.4216 0.01675 0.00995 -0.1270 0.0326 1.0000
8.500 1.4379 0.01723 0.01046 -0.1252 0.0309 1.0000
8.750 1.4522 0.01785 0.01107 -0.1231 0.0289 1.0000
9.000 1.4643 0.01861 0.01187 -0.1207 0.0269 1.0000
9.250 1.4811 0.01909 0.01239 -0.1192 0.0259 1.0000
9.500 1.4966 0.01966 0.01300 -0.1175 0.0246 1.0000
9.750 1.5103 0.02036 0.01370 -0.1155 0.0231 1.0000
10.000 1.5192 0.02138 0.01477 -0.1130 0.0214 1.0000
10.250 1.5347 0.02200 0.01542 -0.1115 0.0207 1.0000
10.500 1.5489 0.02271 0.01618 -0.1098 0.0197 1.0000
10.750 1.5617 0.02354 0.01703 -0.1080 0.0188 1.0000
11.000 1.5709 0.02463 0.01814 -0.1059 0.0176 1.0000
11.250 1.5785 0.02589 0.01947 -0.1036 0.0168 1.0000
11.500 1.5920 0.02673 0.02035 -0.1021 0.0162 1.0000
11.750 1.6031 0.02777 0.02144 -0.1005 0.0155 1.0000
12.000 1.6138 0.02888 0.02259 -0.0988 0.0149 1.0000
12.250 1.6224 0.03019 0.02394 -0.0971 0.0142 1.0000
12.500 1.6221 0.03228 0.02611 -0.0947 0.0135 1.0000
12.750 1.6306 0.03369 0.02759 -0.0932 0.0132 1.0000
13.000 1.6387 0.03519 0.02916 -0.0917 0.0129 1.0000
13.250 1.6459 0.03679 0.03083 -0.0903 0.0125 1.0000
13.500 1.6524 0.03853 0.03264 -0.0890 0.0121 1.0000
13.750 1.6584 0.04038 0.03456 -0.0878 0.0117 1.0000
14.000 1.6632 0.04241 0.03665 -0.0867 0.0114 1.0000
14.250 1.6659 0.04473 0.03904 -0.0856 0.0111 1.0000
14.500 1.6622 0.04787 0.04225 -0.0844 0.0107 1.0000
14.750 1.6583 0.05116 0.04566 -0.0835 0.0104 1.0000
15.000 1.6642 0.05339 0.04797 -0.0830 0.0102 1.0000
15.250 1.6675 0.05598 0.05065 -0.0825 0.0100 1.0000
15.500 1.6695 0.05881 0.05357 -0.0821 0.0098 1.0000
15.750 1.6708 0.06182 0.05668 -0.0819 0.0096 1.0000
16.000 1.6720 0.06489 0.05984 -0.0819 0.0093 1.0000
16.250 1.6717 0.06826 0.06330 -0.0819 0.0092 1.0000
16.500 1.6715 0.07169 0.06681 -0.0822 0.0090 1.0000
16.750 1.6707 0.07528 0.07049 -0.0825 0.0088 1.0000
17.000 1.6685 0.07917 0.07447 -0.0831 0.0087 1.0000
17.250 1.6646 0.08341 0.07880 -0.0839 0.0085 1.0000
17.500 1.6585 0.08808 0.08357 -0.0849 0.0084 1.0000
17.750 1.6493 0.09334 0.08894 -0.0862 0.0082 1.0000
18.000 1.6371 0.09921 0.09494 -0.0878 0.0080 1.0000
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