GOE 527 AIRFOIL (goe527-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 527 AIRFOIL (goe527-il) Reynolds number: 500,000 Max Cl/Cd: 102.34 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe527-il-500000.txt Download as CSV file: xf-goe527-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 527 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1845 0.11133 0.10897 -0.0690 0.9772 0.0429
-12.000 -0.1623 0.10889 0.10652 -0.0708 0.9695 0.0432
-11.750 -0.4754 0.03257 0.02892 -0.1374 0.9316 0.0364
-11.500 -0.4728 0.02929 0.02520 -0.1383 0.9100 0.0368
-11.250 -0.4680 0.02729 0.02283 -0.1369 0.8909 0.0372
-11.000 -0.4613 0.02574 0.02096 -0.1349 0.8742 0.0375
-10.750 -0.4502 0.02475 0.01966 -0.1329 0.8597 0.0378
-10.500 -0.4393 0.02300 0.01769 -0.1311 0.8468 0.0383
-10.250 -0.4220 0.02208 0.01669 -0.1297 0.8346 0.0387
-10.000 -0.4025 0.02145 0.01598 -0.1285 0.8240 0.0393
-9.750 -0.3834 0.02077 0.01516 -0.1273 0.8134 0.0397
-9.500 -0.3640 0.02006 0.01432 -0.1260 0.8033 0.0402
-9.250 -0.3438 0.01935 0.01344 -0.1248 0.7935 0.0407
-9.000 -0.3232 0.01867 0.01263 -0.1236 0.7836 0.0413
-8.750 -0.3017 0.01808 0.01186 -0.1225 0.7746 0.0419
-8.500 -0.2796 0.01754 0.01118 -0.1214 0.7656 0.0424
-8.250 -0.2579 0.01683 0.01032 -0.1203 0.7572 0.0430
-8.000 -0.2355 0.01619 0.00967 -0.1194 0.7488 0.0438
-7.750 -0.2121 0.01578 0.00920 -0.1186 0.7403 0.0446
-7.500 -0.1883 0.01539 0.00874 -0.1177 0.7320 0.0453
-7.250 -0.1645 0.01500 0.00827 -0.1168 0.7234 0.0462
-7.000 -0.1404 0.01464 0.00779 -0.1160 0.7157 0.0471
-6.750 -0.1158 0.01433 0.00739 -0.1152 0.7074 0.0479
-6.250 -0.0684 0.01351 0.00652 -0.1135 0.6918 0.0503
-6.000 -0.0436 0.01329 0.00623 -0.1128 0.6837 0.0518
-5.750 -0.0184 0.01307 0.00594 -0.1121 0.6759 0.0534
-5.500 0.0055 0.01271 0.00555 -0.1112 0.6680 0.0552
-5.250 0.0307 0.01253 0.00534 -0.1106 0.6609 0.0574
-5.000 0.0563 0.01236 0.00512 -0.1099 0.6531 0.0600
-4.750 0.0809 0.01214 0.00487 -0.1092 0.6458 0.0631
-4.500 0.1071 0.01203 0.00473 -0.1087 0.6385 0.0673
-4.250 0.1325 0.01188 0.00459 -0.1081 0.6313 0.0722
-4.000 0.1585 0.01179 0.00446 -0.1075 0.6249 0.0779
-3.750 0.1851 0.01174 0.00441 -0.1071 0.6181 0.0833
-3.500 0.2106 0.01163 0.00426 -0.1065 0.6117 0.0885
-3.250 0.2371 0.01161 0.00421 -0.1061 0.6056 0.0933
-3.000 0.2629 0.01147 0.00406 -0.1056 0.5995 0.0982
-2.750 0.2889 0.01141 0.00397 -0.1051 0.5939 0.1030
-2.500 0.3155 0.01141 0.00391 -0.1047 0.5886 0.1071
-2.250 0.3408 0.01121 0.00375 -0.1041 0.5831 0.1124
-2.000 0.3667 0.01115 0.00366 -0.1036 0.5778 0.1174
-1.750 0.3931 0.01115 0.00358 -0.1032 0.5730 0.1222
-1.500 0.4187 0.01100 0.00350 -0.1027 0.5685 0.1303
-1.250 0.4447 0.01092 0.00343 -0.1022 0.5636 0.1394
-1.000 0.4705 0.01084 0.00337 -0.1017 0.5590 0.1526
-0.750 0.4958 0.01071 0.00336 -0.1012 0.5546 0.1931
-0.500 0.5193 0.01037 0.00337 -0.1005 0.5505 0.2919
-0.250 0.5422 0.01007 0.00339 -0.0996 0.5456 0.3965
0.000 0.5651 0.00987 0.00343 -0.0986 0.5405 0.4899
0.250 0.5882 0.00973 0.00350 -0.0976 0.5357 0.5716
0.500 0.6086 0.00945 0.00356 -0.0960 0.5310 0.6691
0.750 0.6267 0.00912 0.00364 -0.0937 0.5262 0.8015
1.000 0.6810 0.00920 0.00389 -0.0986 0.5199 0.9505
1.250 0.7397 0.00934 0.00401 -0.1050 0.5142 0.9772
1.500 0.7905 0.00947 0.00408 -0.1097 0.5092 0.9889
1.750 0.8410 0.00963 0.00414 -0.1145 0.5045 0.9976
2.000 0.8749 0.00976 0.00421 -0.1159 0.5004 1.0000
2.250 0.8959 0.00982 0.00427 -0.1145 0.4965 1.0000
2.500 0.9168 0.00991 0.00434 -0.1132 0.4925 1.0000
2.750 0.9376 0.01002 0.00440 -0.1117 0.4885 1.0000
3.000 0.9589 0.01020 0.00450 -0.1105 0.4843 1.0000
3.250 0.9795 0.01027 0.00459 -0.1090 0.4806 1.0000
3.500 1.0000 0.01035 0.00467 -0.1075 0.4761 1.0000
3.750 1.0200 0.01046 0.00475 -0.1060 0.4712 1.0000
4.000 1.0403 0.01064 0.00485 -0.1045 0.4663 1.0000
4.250 1.0602 0.01070 0.00495 -0.1029 0.4612 1.0000
4.500 1.0801 0.01081 0.00505 -0.1014 0.4561 1.0000
4.750 1.0997 0.01097 0.00516 -0.0998 0.4513 1.0000
5.000 1.1197 0.01110 0.00529 -0.0983 0.4466 1.0000
5.250 1.1393 0.01121 0.00541 -0.0967 0.4412 1.0000
5.500 1.1574 0.01137 0.00553 -0.0949 0.4356 1.0000
5.750 1.1759 0.01153 0.00569 -0.0931 0.4301 1.0000
6.000 1.1933 0.01166 0.00583 -0.0911 0.4239 1.0000
6.250 1.2077 0.01185 0.00598 -0.0886 0.4180 1.0000
6.500 1.2240 0.01201 0.00616 -0.0864 0.4119 1.0000
6.750 1.2396 0.01220 0.00634 -0.0842 0.4046 1.0000
7.000 1.2542 0.01246 0.00656 -0.0819 0.3979 1.0000
7.250 1.2714 0.01267 0.00679 -0.0800 0.3904 1.0000
7.750 1.3017 0.01327 0.00736 -0.0759 0.3743 1.0000
8.000 1.3139 0.01368 0.00773 -0.0734 0.3652 1.0000
8.250 1.3285 0.01406 0.00810 -0.0714 0.3552 1.0000
8.500 1.3412 0.01453 0.00854 -0.0693 0.3458 1.0000
8.750 1.3528 0.01507 0.00905 -0.0670 0.3363 1.0000
9.000 1.3661 0.01560 0.00957 -0.0651 0.3273 1.0000
9.500 1.3886 0.01691 0.01085 -0.0610 0.3094 1.0000
9.750 1.3971 0.01776 0.01165 -0.0587 0.3009 1.0000
10.000 1.4094 0.01848 0.01238 -0.0571 0.2930 1.0000
10.250 1.4171 0.01946 0.01333 -0.0550 0.2859 1.0000
10.500 1.4305 0.02021 0.01411 -0.0537 0.2799 1.0000
10.750 1.4401 0.02118 0.01508 -0.0520 0.2742 1.0000
11.000 1.4493 0.02223 0.01612 -0.0504 0.2692 1.0000
11.250 1.4622 0.02309 0.01703 -0.0493 0.2646 1.0000
11.500 1.4721 0.02417 0.01812 -0.0479 0.2601 1.0000
11.750 1.4790 0.02546 0.01940 -0.0464 0.2557 1.0000
12.000 1.4913 0.02644 0.02043 -0.0454 0.2523 1.0000
12.250 1.5027 0.02751 0.02156 -0.0444 0.2486 1.0000
12.500 1.5120 0.02875 0.02282 -0.0434 0.2448 1.0000
12.750 1.5181 0.03022 0.02429 -0.0421 0.2410 1.0000
13.000 1.5276 0.03151 0.02562 -0.0412 0.2378 1.0000
13.250 1.5389 0.03269 0.02688 -0.0404 0.2345 1.0000
13.500 1.5475 0.03409 0.02834 -0.0396 0.2310 1.0000
13.750 1.5531 0.03576 0.03001 -0.0387 0.2271 1.0000
14.000 1.5583 0.03748 0.03175 -0.0377 0.2228 1.0000
14.250 1.5666 0.03906 0.03342 -0.0372 0.2182 1.0000
14.500 1.5717 0.04091 0.03530 -0.0365 0.2138 1.0000
14.750 1.5725 0.04311 0.03748 -0.0357 0.2092 1.0000
15.000 1.5803 0.04485 0.03932 -0.0353 0.2047 1.0000
15.250 1.5845 0.04688 0.04141 -0.0348 0.1998 1.0000
15.500 1.5838 0.04939 0.04391 -0.0342 0.1952 1.0000
15.750 1.5892 0.05141 0.04603 -0.0339 0.1906 1.0000
16.000 1.5915 0.05374 0.04840 -0.0336 0.1852 1.0000
16.250 1.5879 0.05667 0.05132 -0.0332 0.1801 1.0000
16.500 1.5922 0.05889 0.05363 -0.0330 0.1746 1.0000
16.750 1.5899 0.06179 0.05655 -0.0328 0.1689 1.0000
17.000 1.5885 0.06462 0.05942 -0.0327 0.1637 1.0000
17.250 1.5876 0.06741 0.06226 -0.0326 0.1587 1.0000
17.500 1.5815 0.07079 0.06564 -0.0325 0.1538 1.0000
17.750 1.5814 0.07356 0.06847 -0.0325 0.1493 1.0000
18.000 1.5784 0.07666 0.07160 -0.0326 0.1452 1.0000
18.250 1.5712 0.08026 0.07520 -0.0327 0.1411 1.0000
18.500 1.5724 0.08289 0.07791 -0.0329 0.1384 1.0000
18.750 1.5700 0.08600 0.08107 -0.0331 0.1349 1.0000
19.000 1.5646 0.08949 0.08457 -0.0335 0.1316 1.0000
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