GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 518 AIRFOIL (goe518-il) Reynolds number: 200,000 Max Cl/Cd: 48.27 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe518-il-200000-n5.txt Download as CSV file: xf-goe518-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 518 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 0.0696 0.11158 0.10766 -0.1093 0.9338 0.0415
-11.500 0.0674 0.10726 0.10333 -0.1142 0.9306 0.0421
-11.250 0.0739 0.10296 0.09903 -0.1186 0.9285 0.0422
-11.000 0.1034 0.10017 0.09623 -0.1191 0.9271 0.0428
-10.750 0.1075 0.09783 0.09391 -0.1185 0.9187 0.0431
-10.500 0.1270 0.09475 0.09081 -0.1211 0.9137 0.0447
-10.250 0.1314 0.08954 0.08557 -0.1288 0.9102 0.0475
-10.000 0.1201 0.08606 0.08211 -0.1300 0.8989 0.0476
-9.750 0.1452 0.08237 0.07839 -0.1331 0.8949 0.0480
-9.500 0.1517 0.08022 0.07625 -0.1323 0.8853 0.0483
-9.250 0.1732 0.07727 0.07328 -0.1353 0.8804 0.0491
-9.000 0.1839 0.07432 0.07033 -0.1375 0.8731 0.0497
-8.750 0.1924 0.07106 0.06705 -0.1402 0.8653 0.0504
-8.500 0.1981 0.06753 0.06350 -0.1434 0.8572 0.0509
-8.250 0.1498 0.05820 0.05404 -0.1492 0.8449 0.0418
-7.750 0.0813 0.04700 0.04239 -0.1426 0.8213 0.0372
-7.500 0.0817 0.04419 0.03942 -0.1406 0.8118 0.0371
-7.250 0.0791 0.04199 0.03707 -0.1373 0.8018 0.0369
-7.000 0.0802 0.03874 0.03354 -0.1348 0.7923 0.0368
-6.750 0.0709 0.03617 0.03071 -0.1295 0.7804 0.0368
-6.500 0.0578 0.03210 0.02598 -0.1236 0.7700 0.0373
-6.250 0.0672 0.03084 0.02460 -0.1206 0.7580 0.0375
-6.000 0.0738 0.02940 0.02295 -0.1169 0.7458 0.0376
-5.750 0.0860 0.02776 0.02102 -0.1143 0.7334 0.0377
-5.500 0.1002 0.02627 0.01921 -0.1118 0.7195 0.0378
-5.250 0.1145 0.02521 0.01793 -0.1093 0.7039 0.0380
-5.000 0.1317 0.02415 0.01661 -0.1072 0.6873 0.0382
-4.750 0.1495 0.02321 0.01540 -0.1052 0.6717 0.0385
-4.500 0.1677 0.02239 0.01432 -0.1032 0.6564 0.0388
-4.250 0.1860 0.02171 0.01340 -0.1012 0.6424 0.0391
-4.000 0.2047 0.02116 0.01261 -0.0993 0.6290 0.0398
-3.750 0.2215 0.02063 0.01187 -0.0969 0.6157 0.0405
-3.500 0.2392 0.02014 0.01116 -0.0948 0.6029 0.0409
-3.250 0.2573 0.01969 0.01049 -0.0926 0.5903 0.0413
-3.000 0.2743 0.01931 0.00995 -0.0903 0.5771 0.0416
-2.750 0.2917 0.01899 0.00948 -0.0881 0.5648 0.0419
-2.500 0.3088 0.01875 0.00907 -0.0858 0.5525 0.0422
-2.250 0.3257 0.01845 0.00872 -0.0836 0.5399 0.0425
-2.000 0.3424 0.01821 0.00844 -0.0814 0.5281 0.0431
-1.750 0.3581 0.01809 0.00823 -0.0789 0.5160 0.0435
-1.500 0.3744 0.01798 0.00807 -0.0766 0.5035 0.0442
-1.250 0.3903 0.01791 0.00793 -0.0742 0.4921 0.0447
-1.000 0.4053 0.01791 0.00783 -0.0717 0.4805 0.0463
-0.750 0.4213 0.01789 0.00773 -0.0694 0.4692 0.0471
-0.500 0.4363 0.01790 0.00765 -0.0669 0.4589 0.0479
-0.250 0.4523 0.01786 0.00758 -0.0647 0.4494 0.0486
0.000 0.4678 0.01789 0.00756 -0.0623 0.4407 0.0496
0.250 0.4843 0.01793 0.00754 -0.0602 0.4321 0.0509
0.500 0.5005 0.01803 0.00755 -0.0580 0.4252 0.0521
0.750 0.5191 0.01809 0.00757 -0.0563 0.4183 0.0537
1.000 0.5363 0.01818 0.00761 -0.0544 0.4118 0.0557
1.250 0.5536 0.01831 0.00768 -0.0525 0.4063 0.0596
1.500 0.5722 0.01836 0.00777 -0.0509 0.4006 0.0671
1.750 0.5900 0.01843 0.00792 -0.0491 0.3954 0.0941
2.000 0.6066 0.01853 0.00807 -0.0472 0.3903 0.1364
2.250 0.6135 0.01755 0.00835 -0.0437 0.3866 0.5332
2.500 0.8464 0.01834 0.00982 -0.0869 0.3738 1.0000
2.750 0.8618 0.01862 0.01000 -0.0848 0.3706 1.0000
3.000 0.8790 0.01884 0.01018 -0.0830 0.3674 1.0000
3.250 0.8958 0.01909 0.01038 -0.0811 0.3642 1.0000
3.500 0.9125 0.01936 0.01059 -0.0793 0.3612 1.0000
3.750 0.9290 0.01966 0.01081 -0.0775 0.3583 1.0000
4.000 0.9460 0.01997 0.01104 -0.0758 0.3558 1.0000
4.250 0.9637 0.02030 0.01128 -0.0742 0.3533 1.0000
4.500 0.9818 0.02059 0.01154 -0.0728 0.3510 1.0000
4.750 0.9993 0.02089 0.01183 -0.0712 0.3483 1.0000
5.000 1.0170 0.02120 0.01212 -0.0697 0.3458 1.0000
5.250 1.0345 0.02153 0.01243 -0.0682 0.3433 1.0000
5.500 1.0521 0.02188 0.01274 -0.0668 0.3410 1.0000
5.750 1.0699 0.02224 0.01305 -0.0654 0.3388 1.0000
6.000 1.0887 0.02261 0.01336 -0.0642 0.3369 1.0000
6.250 1.1092 0.02299 0.01366 -0.0634 0.3350 1.0000
6.500 1.1270 0.02335 0.01406 -0.0621 0.3334 1.0000
6.750 1.1447 0.02374 0.01447 -0.0608 0.3315 1.0000
7.000 1.1628 0.02414 0.01489 -0.0596 0.3298 1.0000
7.250 1.1803 0.02456 0.01532 -0.0584 0.3279 1.0000
7.500 1.1982 0.02498 0.01575 -0.0572 0.3262 1.0000
7.750 1.2156 0.02542 0.01621 -0.0560 0.3244 1.0000
8.000 1.2334 0.02586 0.01665 -0.0550 0.3227 1.0000
8.250 1.2511 0.02631 0.01708 -0.0539 0.3208 1.0000
8.500 1.2708 0.02675 0.01750 -0.0531 0.3192 1.0000
8.750 1.2928 0.02718 0.01787 -0.0527 0.3177 1.0000
9.000 1.3092 0.02770 0.01846 -0.0515 0.3164 1.0000
9.250 1.3243 0.02827 0.01911 -0.0502 0.3149 1.0000
9.500 1.3401 0.02885 0.01975 -0.0491 0.3135 1.0000
9.750 1.3554 0.02945 0.02041 -0.0479 0.3121 1.0000
10.000 1.3705 0.03007 0.02109 -0.0467 0.3105 1.0000
10.250 1.3851 0.03070 0.02178 -0.0455 0.3089 1.0000
10.500 1.3989 0.03135 0.02248 -0.0443 0.3069 1.0000
10.750 1.4141 0.03200 0.02315 -0.0432 0.3055 1.0000
11.000 1.4288 0.03262 0.02379 -0.0421 0.3036 1.0000
11.250 1.4473 0.03315 0.02430 -0.0415 0.3016 1.0000
11.500 1.4661 0.03372 0.02487 -0.0410 0.3000 1.0000
11.750 1.4710 0.03480 0.02611 -0.0390 0.2983 1.0000
12.000 1.4761 0.03593 0.02736 -0.0371 0.2960 1.0000
12.250 1.4847 0.03697 0.02850 -0.0357 0.2942 1.0000
12.500 1.4917 0.03805 0.02967 -0.0341 0.2919 1.0000
12.750 1.5007 0.03908 0.03076 -0.0329 0.2898 1.0000
13.000 1.5112 0.04004 0.03178 -0.0318 0.2880 1.0000
13.250 1.5239 0.04089 0.03265 -0.0310 0.2861 1.0000
13.500 1.5429 0.04139 0.03312 -0.0307 0.2841 1.0000
13.750 1.5377 0.04343 0.03535 -0.0286 0.2818 1.0000
14.000 1.5368 0.04532 0.03740 -0.0270 0.2796 1.0000
14.250 1.5367 0.04723 0.03944 -0.0257 0.2773 1.0000
14.500 1.5392 0.04901 0.04133 -0.0246 0.2752 1.0000
14.750 1.5437 0.05069 0.04310 -0.0237 0.2733 1.0000
15.000 1.5501 0.05221 0.04468 -0.0230 0.2714 1.0000
15.250 1.5612 0.05333 0.04585 -0.0225 0.2697 1.0000
15.500 1.5741 0.05432 0.04686 -0.0222 0.2679 1.0000
15.750 1.5516 0.05870 0.05149 -0.0207 0.2652 1.0000
16.000 1.5326 0.06300 0.05599 -0.0198 0.2621 1.0000
16.250 1.5211 0.06668 0.05981 -0.0193 0.2590 1.0000
16.500 1.5198 0.06929 0.06250 -0.0191 0.2564 1.0000
16.750 1.5348 0.07005 0.06325 -0.0190 0.2541 1.0000
17.000 1.4877 0.07824 0.07171 -0.0189 0.2499 1.0000
17.250 1.4072 0.09130 0.08505 -0.0199 0.2427 1.0000
17.500 1.4257 0.09163 0.08540 -0.0200 0.2404 1.0000
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Polar data table (+)
Polar graphs
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