GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 500 AIRFOIL (goe500-il) Reynolds number: 100,000 Max Cl/Cd: 64.36 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe500-il-100000.txt Download as CSV file: xf-goe500-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3796 0.10792 0.10367 -0.0185 1.0000 0.1043
-7.000 -0.4022 0.10792 0.10376 -0.0164 1.0000 0.1055
-6.750 -0.4129 0.10736 0.10326 -0.0290 0.9950 0.1071
-6.500 -0.3972 0.10145 0.09736 -0.0261 0.9919 0.1085
-6.250 -0.3755 0.09759 0.09345 -0.0242 0.9880 0.1112
-6.000 -0.3524 0.09414 0.08997 -0.0287 0.9827 0.1167
-5.750 -0.3303 0.08893 0.08472 -0.0470 0.9719 0.1235
-5.500 -0.3161 0.08609 0.08189 -0.0420 0.9679 0.1261
-5.250 -0.2705 0.08041 0.07602 -0.0661 0.9577 0.1383
-5.000 -0.2630 0.07728 0.07295 -0.0602 0.9527 0.1397
-4.750 -0.2512 0.07524 0.07092 -0.0565 0.9464 0.1432
-4.500 -0.2079 0.07029 0.06583 -0.0688 0.9410 0.1562
-4.250 -0.1818 0.06747 0.06291 -0.0745 0.9322 0.1678
-4.000 -0.0810 0.04835 0.04257 -0.1092 0.9301 0.1224
-3.750 -0.0199 0.03900 0.03219 -0.1208 0.9284 0.1068
-3.500 0.0289 0.03572 0.02856 -0.1265 0.9253 0.1103
-3.250 0.0556 0.03443 0.02708 -0.1272 0.9162 0.1145
-3.000 0.1050 0.03210 0.02407 -0.1318 0.9116 0.1194
-2.750 0.1390 0.03084 0.02253 -0.1334 0.9044 0.1273
-2.500 0.1779 0.02982 0.02113 -0.1354 0.8979 0.1390
-2.250 0.2239 0.02880 0.02010 -0.1388 0.8941 0.1571
-2.000 0.2450 0.02850 0.01978 -0.1379 0.8844 0.1732
-1.750 0.2880 0.02807 0.01925 -0.1405 0.8797 0.1995
-1.500 0.3113 0.02800 0.01924 -0.1399 0.8706 0.2178
-1.250 0.3507 0.02769 0.01901 -0.1419 0.8653 0.2412
-1.000 0.3776 0.02765 0.01894 -0.1418 0.8570 0.2612
-0.750 0.4146 0.02728 0.01866 -0.1433 0.8510 0.2859
-0.500 0.4488 0.02696 0.01845 -0.1443 0.8447 0.3198
-0.250 0.4790 0.02664 0.01832 -0.1445 0.8368 0.3755
0.000 0.5237 0.02600 0.01798 -0.1470 0.8333 0.4582
0.250 0.5433 0.02615 0.01827 -0.1455 0.8226 0.5114
0.500 0.5877 0.02550 0.01782 -0.1477 0.8190 0.5867
0.750 0.6093 0.02542 0.01796 -0.1465 0.8087 0.6609
1.000 0.6530 0.02416 0.01718 -0.1482 0.8049 1.0000
1.250 0.6792 0.02441 0.01726 -0.1480 0.7952 1.0000
1.500 0.7225 0.02401 0.01672 -0.1501 0.7906 1.0000
1.750 0.7647 0.02356 0.01616 -0.1519 0.7864 1.0000
2.000 0.7902 0.02369 0.01623 -0.1513 0.7761 1.0000
2.250 0.8355 0.02301 0.01549 -0.1534 0.7730 1.0000
2.500 0.8564 0.02336 0.01582 -0.1521 0.7614 1.0000
2.750 0.9010 0.02267 0.01509 -0.1540 0.7580 1.0000
3.000 0.9227 0.02299 0.01541 -0.1528 0.7463 1.0000
3.250 0.9674 0.02227 0.01468 -0.1548 0.7425 1.0000
3.500 0.9881 0.02269 0.01511 -0.1535 0.7306 1.0000
3.750 1.0169 0.02276 0.01522 -0.1533 0.7216 1.0000
4.000 1.0526 0.02249 0.01495 -0.1540 0.7143 1.0000
4.250 1.0766 0.02284 0.01535 -0.1532 0.7038 1.0000
4.500 1.1157 0.02246 0.01500 -0.1543 0.6975 1.0000
4.750 1.1369 0.02292 0.01552 -0.1531 0.6858 1.0000
5.000 1.1664 0.02288 0.01552 -0.1528 0.6755 1.0000
5.250 1.2035 0.02246 0.01511 -0.1535 0.6663 1.0000
5.500 1.2244 0.02288 0.01563 -0.1521 0.6542 1.0000
5.750 1.2496 0.02320 0.01604 -0.1514 0.6440 1.0000
6.000 1.2827 0.02293 0.01578 -0.1514 0.6329 1.0000
6.250 1.3098 0.02268 0.01558 -0.1504 0.6176 1.0000
6.500 1.3317 0.02245 0.01540 -0.1484 0.5984 1.0000
6.750 1.3553 0.02210 0.01504 -0.1466 0.5778 1.0000
7.000 1.3780 0.02182 0.01474 -0.1447 0.5558 1.0000
7.250 1.3943 0.02190 0.01488 -0.1421 0.5336 1.0000
7.500 1.4140 0.02197 0.01496 -0.1401 0.5124 1.0000
7.750 1.4264 0.02226 0.01533 -0.1370 0.4877 1.0000
8.000 1.4372 0.02259 0.01566 -0.1335 0.4586 1.0000
8.250 1.4419 0.02312 0.01614 -0.1291 0.4218 1.0000
8.500 1.4346 0.02398 0.01687 -0.1230 0.3707 1.0000
8.750 1.4142 0.02570 0.01806 -0.1155 0.2775 1.0000
9.000 1.3885 0.02873 0.02030 -0.1087 0.1914 1.0000
9.250 1.3694 0.03198 0.02300 -0.1035 0.1394 1.0000
9.500 1.3602 0.03472 0.02555 -0.0996 0.1184 1.0000
9.750 1.3553 0.03724 0.02800 -0.0965 0.1070 1.0000
10.000 1.3513 0.03982 0.03049 -0.0936 0.0989 1.0000
10.250 1.3560 0.04186 0.03260 -0.0914 0.0916 1.0000
10.500 1.3603 0.04417 0.03475 -0.0893 0.0858 1.0000
10.750 1.3721 0.04588 0.03662 -0.0876 0.0801 1.0000
11.000 1.3893 0.04763 0.03823 -0.0863 0.0749 1.0000
11.250 1.4162 0.04923 0.03990 -0.0854 0.0702 1.0000
11.500 1.4375 0.05097 0.04170 -0.0845 0.0658 1.0000
11.750 1.4965 0.05355 0.04422 -0.0865 0.0612 1.0000
12.000 1.5107 0.05591 0.04692 -0.0850 0.0591 1.0000
12.250 1.5245 0.05850 0.04978 -0.0837 0.0568 1.0000
12.500 1.5416 0.06157 0.05310 -0.0828 0.0553 1.0000
12.750 1.5548 0.06500 0.05681 -0.0816 0.0545 1.0000
13.000 1.5617 0.06858 0.06067 -0.0802 0.0536 1.0000
13.250 1.5662 0.07261 0.06492 -0.0789 0.0526 1.0000
13.500 1.5684 0.07812 0.07069 -0.0780 0.0518 1.0000
13.750 1.5573 0.08329 0.07617 -0.0762 0.0515 1.0000
14.000 1.5410 0.08783 0.08098 -0.0744 0.0515 1.0000
14.250 1.5231 0.09189 0.08536 -0.0729 0.0516 1.0000
14.500 1.5029 0.09589 0.08965 -0.0718 0.0518 1.0000
14.750 1.4785 0.10028 0.09434 -0.0715 0.0522 1.0000
15.000 1.4457 0.10585 0.10028 -0.0724 0.0529 1.0000
15.250 1.3679 0.11796 0.11300 -0.0785 0.0559 1.0000
15.500 1.3287 0.12846 0.12378 -0.0844 0.0576 1.0000
15.750 1.2967 0.13909 0.13458 -0.0909 0.0592 1.0000
16.000 1.2729 0.14927 0.14486 -0.0972 0.0606 1.0000
16.250 1.2596 0.15807 0.15370 -0.1020 0.0616 1.0000
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Polar data table (+)
Polar graphs
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