GOE 418 AIRFOIL (goe418-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 418 AIRFOIL (goe418-il) Reynolds number: 200,000 Max Cl/Cd: 75.06 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe418-il-200000.txt Download as CSV file: xf-goe418-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 418 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2467 0.10052 0.09682 -0.0341 1.0000 0.0864
-8.750 -0.2807 0.10010 0.09651 -0.0328 1.0000 0.0883
-8.500 -0.2979 0.09623 0.09270 -0.0393 0.9951 0.0891
-8.250 -0.2642 0.09252 0.08898 -0.0393 0.9929 0.0897
-8.000 -0.2345 0.08923 0.08569 -0.0412 0.9883 0.0908
-7.750 -0.2072 0.08582 0.08228 -0.0455 0.9827 0.0928
-7.500 -0.2099 0.07730 0.07367 -0.0712 0.9597 0.0983
-7.250 -0.1804 0.07438 0.07079 -0.0689 0.9565 0.0989
-7.000 -0.1474 0.07161 0.06802 -0.0696 0.9533 0.0999
-6.750 -0.1194 0.06868 0.06508 -0.0725 0.9437 0.1016
-6.500 -0.0889 0.06446 0.06081 -0.0812 0.9334 0.1061
-6.250 -0.0689 0.05724 0.05339 -0.0947 0.9160 0.1101
-6.000 -0.0418 0.05509 0.05122 -0.0954 0.9029 0.1114
-5.750 -0.0204 0.05292 0.04898 -0.0965 0.8856 0.1135
-5.500 -0.0120 0.04667 0.04224 -0.1050 0.8640 0.1218
-5.250 0.0069 0.04523 0.04084 -0.1033 0.8472 0.1228
-5.000 0.0097 0.03519 0.02996 -0.1074 0.8302 0.1096
-4.750 0.0312 0.03328 0.02795 -0.1068 0.8157 0.1070
-4.500 0.0497 0.03000 0.02431 -0.1067 0.8030 0.1060
-4.250 0.0673 0.02673 0.02058 -0.1061 0.7893 0.1058
-4.000 0.0880 0.02433 0.01759 -0.1054 0.7774 0.1079
-3.750 0.1111 0.02264 0.01559 -0.1048 0.7668 0.1101
-3.500 0.1359 0.02212 0.01510 -0.1042 0.7549 0.1120
-3.250 0.1622 0.02144 0.01425 -0.1037 0.7458 0.1145
-3.000 0.1866 0.02064 0.01323 -0.1029 0.7343 0.1178
-2.750 0.2130 0.02011 0.01227 -0.1022 0.7244 0.1207
-2.500 0.2372 0.01891 0.01102 -0.1016 0.7136 0.1235
-2.250 0.2638 0.01858 0.01065 -0.1011 0.7046 0.1268
-2.000 0.2899 0.01819 0.01015 -0.1005 0.6954 0.1305
-1.500 0.3430 0.01718 0.00885 -0.0994 0.6798 0.1375
-1.250 0.3700 0.01692 0.00856 -0.0990 0.6723 0.1414
-1.000 0.3970 0.01671 0.00826 -0.0985 0.6651 0.1454
-0.750 0.4238 0.01658 0.00802 -0.0980 0.6573 0.1490
-0.500 0.4511 0.01610 0.00749 -0.0976 0.6508 0.1531
-0.250 0.4773 0.01592 0.00736 -0.0971 0.6434 0.1572
0.000 0.5040 0.01578 0.00719 -0.0965 0.6355 0.1616
0.250 0.5315 0.01573 0.00702 -0.0961 0.6281 0.1654
0.500 0.5567 0.01541 0.00676 -0.0953 0.6193 0.1698
0.750 0.5837 0.01528 0.00662 -0.0948 0.6116 0.1746
1.000 0.6092 0.01519 0.00657 -0.0940 0.6031 0.1794
1.250 0.6356 0.01513 0.00646 -0.0934 0.5950 0.1844
1.500 0.6617 0.01499 0.00638 -0.0928 0.5879 0.1910
1.750 0.6868 0.01491 0.00637 -0.0920 0.5794 0.1981
2.000 0.7133 0.01483 0.00629 -0.0914 0.5719 0.2078
2.250 0.7377 0.01476 0.00632 -0.0904 0.5626 0.2220
2.500 0.7628 0.01460 0.00629 -0.0896 0.5542 0.2499
2.750 0.7833 0.01396 0.00636 -0.0882 0.5459 0.4502
3.000 0.8417 0.01299 0.00634 -0.0939 0.5350 1.0000
3.250 0.8659 0.01314 0.00643 -0.0929 0.5262 1.0000
3.500 0.8900 0.01325 0.00646 -0.0918 0.5168 1.0000
3.750 0.9140 0.01340 0.00655 -0.0908 0.5074 1.0000
4.000 0.9380 0.01353 0.00661 -0.0898 0.4979 1.0000
4.250 0.9616 0.01368 0.00674 -0.0887 0.4880 1.0000
4.500 0.9854 0.01383 0.00680 -0.0877 0.4782 1.0000
4.750 1.0083 0.01399 0.00696 -0.0865 0.4673 1.0000
5.000 1.0319 0.01417 0.00703 -0.0855 0.4575 1.0000
5.250 1.0540 0.01432 0.00720 -0.0842 0.4452 1.0000
5.500 1.0764 0.01452 0.00736 -0.0830 0.4341 1.0000
5.750 1.0987 0.01474 0.00750 -0.0818 0.4234 1.0000
6.000 1.1207 0.01497 0.00774 -0.0805 0.4120 1.0000
6.250 1.1424 0.01523 0.00795 -0.0793 0.4014 1.0000
6.500 1.1635 0.01550 0.00819 -0.0779 0.3901 1.0000
6.750 1.1843 0.01579 0.00847 -0.0765 0.3786 1.0000
7.000 1.2040 0.01613 0.00875 -0.0750 0.3671 1.0000
7.250 1.2229 0.01648 0.00907 -0.0734 0.3544 1.0000
7.500 1.2410 0.01684 0.00942 -0.0716 0.3405 1.0000
7.750 1.2573 0.01726 0.00981 -0.0696 0.3256 1.0000
8.000 1.2715 0.01774 0.01025 -0.0672 0.3084 1.0000
8.250 1.2828 0.01830 0.01074 -0.0644 0.2882 1.0000
8.500 1.2880 0.01898 0.01129 -0.0607 0.2664 1.0000
8.750 1.2934 0.01973 0.01195 -0.0571 0.2429 1.0000
9.000 1.2980 0.02062 0.01272 -0.0537 0.2247 1.0000
9.250 1.3042 0.02154 0.01356 -0.0507 0.2122 1.0000
9.750 1.3201 0.02345 0.01536 -0.0457 0.1960 1.0000
10.000 1.3275 0.02452 0.01636 -0.0433 0.1902 1.0000
10.250 1.3379 0.02550 0.01734 -0.0414 0.1856 1.0000
10.500 1.3490 0.02645 0.01832 -0.0397 0.1811 1.0000
10.750 1.3584 0.02756 0.01939 -0.0379 0.1770 1.0000
11.000 1.3688 0.02871 0.02048 -0.0363 0.1734 1.0000
11.250 1.3811 0.02968 0.02155 -0.0349 0.1702 1.0000
11.500 1.3929 0.03073 0.02264 -0.0336 0.1671 1.0000
11.750 1.4043 0.03183 0.02376 -0.0323 0.1643 1.0000
12.000 1.4166 0.03301 0.02484 -0.0310 0.1608 1.0000
12.250 1.4281 0.03416 0.02607 -0.0298 0.1580 1.0000
12.500 1.4381 0.03538 0.02738 -0.0287 0.1551 1.0000
12.750 1.4482 0.03663 0.02869 -0.0276 0.1521 1.0000
13.000 1.4594 0.03787 0.02994 -0.0266 0.1495 1.0000
13.250 1.4786 0.03881 0.03075 -0.0258 0.1462 1.0000
13.500 1.4848 0.04032 0.03244 -0.0247 0.1444 1.0000
13.750 1.4918 0.04186 0.03411 -0.0238 0.1420 1.0000
14.000 1.4995 0.04339 0.03572 -0.0229 0.1393 1.0000
14.250 1.5083 0.04487 0.03722 -0.0222 0.1364 1.0000
14.500 1.5262 0.04589 0.03814 -0.0214 0.1329 1.0000
14.750 1.5243 0.04815 0.04061 -0.0207 0.1307 1.0000
15.000 1.5251 0.05033 0.04294 -0.0202 0.1278 1.0000
15.250 1.5288 0.05232 0.04498 -0.0197 0.1246 1.0000
15.500 1.5442 0.05344 0.04597 -0.0190 0.1206 1.0000
15.750 1.5353 0.05665 0.04945 -0.0190 0.1182 1.0000
16.000 1.5316 0.05956 0.05252 -0.0190 0.1148 1.0000
16.250 1.5329 0.06200 0.05497 -0.0190 0.1113 1.0000
16.500 1.5316 0.06485 0.05788 -0.0191 0.1074 1.0000
16.750 1.5216 0.06884 0.06208 -0.0199 0.1036 1.0000
17.000 1.5192 0.07196 0.06520 -0.0205 0.0998 1.0000
17.250 1.5110 0.07602 0.06940 -0.0214 0.0958 1.0000
17.500 1.5022 0.08035 0.07387 -0.0228 0.0918 1.0000
17.750 1.5018 0.08345 0.07690 -0.0236 0.0885 1.0000
18.000 1.4884 0.08881 0.08253 -0.0255 0.0847 1.0000
18.250 1.4838 0.09283 0.08662 -0.0269 0.0818 1.0000
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Polar data table (+)
Polar graphs
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