GOE 562 AIRFOIL (goe562-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 562 AIRFOIL (goe562-il) Reynolds number: 200,000 Max Cl/Cd: 70.43 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe562-il-200000.txt Download as CSV file: xf-goe562-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 562 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2218 0.12366 0.12048 -0.0371 1.0000 0.0347
-10.500 -0.2207 0.12116 0.11804 -0.0371 1.0000 0.0352
-10.250 -0.2219 0.11872 0.11567 -0.0370 1.0000 0.0364
-10.000 -0.2176 0.11567 0.11267 -0.0427 0.9975 0.0379
-9.750 -0.2045 0.11124 0.10825 -0.0537 0.9907 0.0383
-9.500 -0.1803 0.10483 0.10183 -0.0564 0.9863 0.0390
-9.250 -0.1538 0.10029 0.09727 -0.0589 0.9771 0.0399
-9.000 -0.1442 0.09686 0.09388 -0.0599 0.9389 0.0407
-8.750 -0.1213 0.09231 0.08929 -0.0654 0.9189 0.0424
-8.500 -0.0913 0.08692 0.08382 -0.0750 0.9037 0.0447
-8.250 -0.0616 0.07939 0.07612 -0.1009 0.8817 0.0468
-8.000 -0.0046 0.07258 0.06919 -0.1059 0.8670 0.0489
-7.750 0.0550 0.06680 0.06315 -0.1206 0.8392 0.0521
-7.500 0.0739 0.06245 0.05854 -0.1294 0.8064 0.0550
-7.250 0.0634 0.05945 0.05512 -0.1348 0.7809 0.0572
-7.000 0.0607 0.05540 0.05085 -0.1343 0.7637 0.0579
-6.750 0.0753 0.05234 0.04779 -0.1335 0.7481 0.0588
-6.500 0.0883 0.05061 0.04599 -0.1322 0.7346 0.0604
-6.250 0.0976 0.04886 0.04412 -0.1309 0.7222 0.0628
-6.000 0.1043 0.04673 0.04183 -0.1298 0.7113 0.0661
-5.750 0.0995 0.04398 0.03849 -0.1271 0.7035 0.0709
-5.500 0.1129 0.04140 0.03597 -0.1261 0.6938 0.0722
-5.250 0.1276 0.03975 0.03424 -0.1248 0.6855 0.0743
-5.000 0.1401 0.03821 0.03257 -0.1230 0.6770 0.0782
-4.750 0.1462 0.03626 0.03013 -0.1199 0.6704 0.0859
-4.500 0.1623 0.03459 0.02852 -0.1187 0.6622 0.0891
-4.250 0.1743 0.03372 0.02716 -0.1160 0.6562 0.1006
-4.000 0.1904 0.03180 0.02536 -0.1147 0.6488 0.1038
-3.750 0.2043 0.03104 0.02422 -0.1122 0.6429 0.1164
-3.500 0.2228 0.02942 0.02267 -0.1111 0.6365 0.1211
-3.250 0.2376 0.02836 0.02143 -0.1089 0.6301 0.1348
-3.000 0.2565 0.02740 0.02029 -0.1076 0.6248 0.1507
-2.750 0.2712 0.02648 0.01937 -0.1054 0.6183 0.1678
-2.500 0.2892 0.02561 0.01845 -0.1038 0.6127 0.1873
-2.250 0.3287 0.02182 0.01317 -0.1009 0.6090 0.0809
-2.000 0.3516 0.02055 0.01169 -0.0995 0.6034 0.0758
-1.750 0.3770 0.01977 0.01070 -0.0986 0.5979 0.0749
-1.500 0.4068 0.01913 0.00977 -0.0986 0.5932 0.0726
-1.250 0.4312 0.01862 0.00919 -0.0976 0.5876 0.0721
-1.000 0.4573 0.01815 0.00866 -0.0971 0.5823 0.0720
-0.750 0.4859 0.01766 0.00811 -0.0972 0.5778 0.0733
-0.500 0.5090 0.01736 0.00785 -0.0962 0.5727 0.0756
-0.250 0.5310 0.01709 0.00759 -0.0949 0.5669 0.0786
0.000 0.5563 0.01684 0.00724 -0.0943 0.5619 0.0812
0.250 0.5771 0.01670 0.00710 -0.0927 0.5567 0.0835
0.500 0.5970 0.01646 0.00688 -0.0910 0.5512 0.0883
0.750 0.6218 0.01636 0.00669 -0.0903 0.5466 0.0981
1.000 0.6424 0.01613 0.00665 -0.0888 0.5416 0.1439
1.250 0.8691 0.01473 0.00687 -0.1326 0.5277 1.0000
1.500 0.8884 0.01487 0.00701 -0.1310 0.5226 1.0000
1.750 0.9105 0.01500 0.00707 -0.1299 0.5180 1.0000
2.000 0.9349 0.01515 0.00710 -0.1292 0.5142 1.0000
2.250 0.9556 0.01533 0.00727 -0.1279 0.5097 1.0000
2.500 0.9760 0.01549 0.00742 -0.1265 0.5049 1.0000
2.750 0.9990 0.01563 0.00749 -0.1256 0.5007 1.0000
3.000 1.0235 0.01582 0.00759 -0.1250 0.4968 1.0000
3.250 1.0414 0.01601 0.00784 -0.1231 0.4918 1.0000
3.500 1.0627 0.01616 0.00797 -0.1219 0.4872 1.0000
3.750 1.0867 0.01632 0.00806 -0.1212 0.4831 1.0000
4.000 1.1060 0.01654 0.00831 -0.1196 0.4784 1.0000
4.250 1.1252 0.01672 0.00851 -0.1180 0.4732 1.0000
4.500 1.1478 0.01686 0.00860 -0.1170 0.4686 1.0000
4.750 1.1680 0.01708 0.00882 -0.1157 0.4638 1.0000
5.000 1.1855 0.01727 0.00907 -0.1137 0.4582 1.0000
5.250 1.2070 0.01741 0.00916 -0.1126 0.4532 1.0000
5.500 1.2259 0.01764 0.00942 -0.1109 0.4479 1.0000
5.750 1.2426 0.01783 0.00967 -0.1089 0.4420 1.0000
6.000 1.2641 0.01800 0.00979 -0.1077 0.4369 1.0000
6.250 1.2795 0.01826 0.01012 -0.1054 0.4308 1.0000
6.500 1.2962 0.01845 0.01035 -0.1034 0.4246 1.0000
6.750 1.3164 0.01869 0.01055 -0.1021 0.4191 1.0000
7.000 1.3281 0.01895 0.01092 -0.0990 0.4120 1.0000
7.250 1.3471 0.01917 0.01108 -0.0975 0.4059 1.0000
7.500 1.3579 0.01949 0.01152 -0.0944 0.3987 1.0000
7.750 1.3730 0.01975 0.01177 -0.0921 0.3920 1.0000
8.000 1.3839 0.02009 0.01217 -0.0890 0.3846 1.0000
8.250 1.3935 0.02033 0.01241 -0.0857 0.3773 1.0000
8.500 1.3981 0.02061 0.01274 -0.0814 0.3693 1.0000
8.750 1.4036 0.02084 0.01294 -0.0773 0.3613 1.0000
9.000 1.4083 0.02121 0.01340 -0.0733 0.3532 1.0000
9.250 1.4157 0.02156 0.01369 -0.0698 0.3456 1.0000
9.500 1.4228 0.02206 0.01431 -0.0665 0.3385 1.0000
9.750 1.4316 0.02254 0.01478 -0.0636 0.3322 1.0000
10.000 1.4383 0.02312 0.01544 -0.0605 0.3252 1.0000
10.250 1.4444 0.02372 0.01606 -0.0574 0.3182 1.0000
10.500 1.4508 0.02441 0.01682 -0.0545 0.3117 1.0000
10.750 1.4555 0.02519 0.01764 -0.0516 0.3046 1.0000
11.000 1.4617 0.02603 0.01852 -0.0490 0.2989 1.0000
11.250 1.4650 0.02703 0.01962 -0.0463 0.2916 1.0000
11.500 1.4662 0.02821 0.02083 -0.0436 0.2841 1.0000
11.750 1.4674 0.02953 0.02224 -0.0412 0.2764 1.0000
12.000 1.4670 0.03107 0.02383 -0.0388 0.2686 1.0000
12.250 1.4644 0.03287 0.02566 -0.0366 0.2601 1.0000
12.500 1.4605 0.03495 0.02783 -0.0347 0.2504 1.0000
12.750 1.4531 0.03745 0.03036 -0.0328 0.2403 1.0000
13.000 1.4428 0.04040 0.03332 -0.0311 0.2292 1.0000
13.250 1.4286 0.04396 0.03692 -0.0298 0.2149 1.0000
13.500 1.4114 0.04811 0.04111 -0.0287 0.1926 1.0000
13.750 1.3866 0.05319 0.04609 -0.0279 0.1469 1.0000
14.000 1.3583 0.05884 0.05156 -0.0272 0.1185 1.0000
14.250 1.3323 0.06445 0.05710 -0.0267 0.0970 1.0000
14.500 1.3011 0.07092 0.06348 -0.0266 0.0718 1.0000
14.750 1.2756 0.07705 0.06961 -0.0267 0.0598 1.0000
15.000 1.2564 0.08261 0.07524 -0.0271 0.0525 1.0000
15.250 1.2380 0.08825 0.08096 -0.0277 0.0483 1.0000
15.500 1.2204 0.09394 0.08678 -0.0285 0.0433 1.0000
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