GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 431 AIRFOIL (goe431-il) Reynolds number: 100,000 Max Cl/Cd: 55.74 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe431-il-100000-n5.txt Download as CSV file: xf-goe431-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 431 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1046 0.09928 0.09414 -0.0958 0.9374 0.0302
-9.500 -0.1005 0.09541 0.09028 -0.0979 0.9331 0.0302
-9.250 -0.1038 0.09073 0.08563 -0.1001 0.9271 0.0311
-9.000 -0.1024 0.08499 0.07990 -0.1041 0.9234 0.0315
-8.750 -0.1126 0.07804 0.07297 -0.1083 0.9184 0.0318
-8.500 -0.1251 0.07456 0.06953 -0.1081 0.9109 0.0316
-8.250 -0.1445 0.06673 0.06168 -0.1138 0.9055 0.0316
-8.000 -0.1700 0.06372 0.05870 -0.1121 0.8953 0.0314
-7.750 -0.1746 0.05260 0.04730 -0.1273 0.8902 0.0313
-7.500 -0.1868 0.04837 0.04293 -0.1302 0.8811 0.0313
-7.250 -0.1567 0.04172 0.03589 -0.1425 0.8784 0.0323
-7.000 -0.1241 0.03891 0.03294 -0.1483 0.8768 0.0340
-6.750 -0.0830 0.03526 0.02895 -0.1569 0.8758 0.0374
-6.500 -0.0584 0.03317 0.02658 -0.1602 0.8725 0.0406
-6.250 -0.0353 0.03173 0.02500 -0.1622 0.8687 0.0443
-6.000 -0.0011 0.02993 0.02290 -0.1660 0.8667 0.0506
-5.750 0.0360 0.02797 0.02066 -0.1706 0.8653 0.0619
-5.500 0.0721 0.02643 0.01918 -0.1744 0.8642 0.0825
-5.250 0.0995 0.02733 0.02033 -0.1741 0.8626 0.1152
-5.000 0.1308 0.02781 0.02044 -0.1749 0.8613 0.1429
-4.750 0.1610 0.02833 0.02080 -0.1752 0.8602 0.1563
-4.500 0.1695 0.02865 0.02076 -0.1727 0.8547 0.1652
-4.250 0.1919 0.02909 0.02131 -0.1715 0.8510 0.1711
-4.000 0.2298 0.02866 0.02046 -0.1735 0.8483 0.1813
-3.750 0.2690 0.02859 0.02052 -0.1748 0.8458 0.1893
-3.500 0.2856 0.02863 0.02030 -0.1733 0.8390 0.1963
-3.250 0.3205 0.02807 0.01965 -0.1743 0.8343 0.2009
-3.000 0.3650 0.02715 0.01854 -0.1770 0.8316 0.2042
-2.750 0.4125 0.02611 0.01726 -0.1803 0.8297 0.2065
-2.500 0.4182 0.02634 0.01740 -0.1767 0.8212 0.2073
-2.250 0.4556 0.02566 0.01651 -0.1783 0.8180 0.2089
-2.000 0.4970 0.02492 0.01558 -0.1806 0.8157 0.2105
-1.750 0.5247 0.02463 0.01515 -0.1805 0.8112 0.2120
-1.500 0.5442 0.02457 0.01497 -0.1790 0.8045 0.2133
-1.250 0.5818 0.02399 0.01438 -0.1804 0.8013 0.2154
-1.000 0.6228 0.02334 0.01370 -0.1824 0.7988 0.2181
-0.750 0.6318 0.02366 0.01403 -0.1791 0.7900 0.2199
-0.500 0.6674 0.02316 0.01348 -0.1801 0.7859 0.2225
-0.250 0.7083 0.02250 0.01275 -0.1820 0.7829 0.2254
0.000 0.7190 0.02270 0.01295 -0.1788 0.7728 0.2274
0.250 0.7581 0.02206 0.01231 -0.1803 0.7682 0.2306
0.500 0.7722 0.02215 0.01246 -0.1777 0.7586 0.2331
1.000 0.8207 0.02172 0.01208 -0.1757 0.7418 0.2415
1.250 0.8546 0.02121 0.01161 -0.1762 0.7341 0.2477
1.750 0.8831 0.02140 0.01191 -0.1709 0.7072 0.2612
2.250 0.9077 0.02194 0.01260 -0.1654 0.6666 0.2793
2.500 0.9268 0.02194 0.01263 -0.1636 0.6346 0.2938
2.750 0.9769 0.02049 0.01106 -0.1660 0.5880 0.3255
3.000 1.0241 0.01961 0.00980 -0.1681 0.5378 0.3724
3.250 1.0475 0.01992 0.00993 -0.1671 0.5076 0.4195
3.500 1.0690 0.02034 0.01028 -0.1659 0.4877 0.4724
4.000 1.1155 0.02109 0.01099 -0.1642 0.4613 0.5668
4.250 1.1404 0.02135 0.01130 -0.1637 0.4521 0.6121
4.500 1.1631 0.02127 0.01157 -0.1626 0.4444 0.7431
4.750 1.1867 0.02152 0.01181 -0.1619 0.4377 1.0000
5.000 1.2132 0.02194 0.01218 -0.1617 0.4314 1.0000
5.250 1.2417 0.02239 0.01252 -0.1619 0.4262 1.0000
5.500 1.2683 0.02282 0.01296 -0.1618 0.4210 1.0000
5.750 1.2945 0.02326 0.01341 -0.1616 0.4159 1.0000
6.000 1.3224 0.02374 0.01385 -0.1618 0.4114 1.0000
6.250 1.3506 0.02423 0.01436 -0.1620 0.4075 1.0000
6.500 1.3756 0.02471 0.01492 -0.1616 0.4032 1.0000
6.750 1.4005 0.02522 0.01547 -0.1613 0.3985 1.0000
7.000 1.4276 0.02577 0.01599 -0.1613 0.3938 1.0000
7.250 1.4482 0.02629 0.01665 -0.1602 0.3886 1.0000
7.500 1.4699 0.02683 0.01728 -0.1593 0.3833 1.0000
7.750 1.4947 0.02738 0.01786 -0.1590 0.3788 1.0000
8.000 1.5164 0.02796 0.01855 -0.1581 0.3742 1.0000
8.250 1.5355 0.02854 0.01930 -0.1568 0.3693 1.0000
8.500 1.5574 0.02912 0.01999 -0.1560 0.3648 1.0000
8.750 1.5819 0.02973 0.02063 -0.1556 0.3605 1.0000
9.000 1.5946 0.03038 0.02152 -0.1533 0.3551 1.0000
9.250 1.6109 0.03100 0.02229 -0.1516 0.3495 1.0000
9.500 1.6262 0.03163 0.02301 -0.1497 0.3430 1.0000
9.750 1.6306 0.03236 0.02395 -0.1463 0.3345 1.0000
10.000 1.6358 0.03310 0.02476 -0.1430 0.3251 1.0000
10.250 1.6362 0.03397 0.02574 -0.1393 0.3142 1.0000
10.500 1.6359 0.03501 0.02695 -0.1356 0.3025 1.0000
10.750 1.6362 0.03614 0.02822 -0.1323 0.2899 1.0000
11.000 1.6364 0.03741 0.02964 -0.1292 0.2757 1.0000
11.250 1.6370 0.03883 0.03122 -0.1264 0.2582 1.0000
11.500 1.6369 0.04045 0.03297 -0.1237 0.2327 1.0000
11.750 1.6282 0.04278 0.03511 -0.1205 0.1932 1.0000
12.000 1.6129 0.04608 0.03812 -0.1172 0.1646 1.0000
12.250 1.5997 0.04965 0.04156 -0.1145 0.1416 1.0000
12.500 1.5875 0.05340 0.04527 -0.1123 0.1154 1.0000
12.750 1.5708 0.05786 0.04964 -0.1103 0.0845 1.0000
13.000 1.5489 0.06320 0.05486 -0.1087 0.0607 1.0000
13.250 1.5292 0.06867 0.06033 -0.1078 0.0500 1.0000
13.500 1.5109 0.07435 0.06609 -0.1075 0.0442 1.0000
13.750 1.4946 0.08015 0.07203 -0.1077 0.0403 1.0000
14.000 1.4781 0.08636 0.07840 -0.1086 0.0376 1.0000
14.250 1.4616 0.09296 0.08514 -0.1100 0.0358 1.0000
14.500 1.4472 0.09946 0.09180 -0.1117 0.0342 1.0000
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Polar data table (+)
Polar graphs
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