GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 286 AIRFOIL (goe286-il) Reynolds number: 500,000 Max Cl/Cd: 83.57 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe286-il-500000.txt Download as CSV file: xf-goe286-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 286 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3863 0.09102 0.08888 -0.0142 1.0000 0.0245
-8.000 -0.3824 0.08726 0.08514 -0.0173 1.0000 0.0256
-7.750 -0.3811 0.08131 0.07922 -0.0280 1.0000 0.0265
-7.500 -0.3713 0.07599 0.07389 -0.0349 1.0000 0.0266
-7.250 -0.3660 0.07150 0.06937 -0.0384 1.0000 0.0266
-7.000 -0.3653 0.06706 0.06496 -0.0385 0.9985 0.0271
-6.750 -0.3389 0.06404 0.06192 -0.0421 0.9949 0.0276
-6.500 -0.3106 0.06071 0.05855 -0.0467 0.9894 0.0285
-6.250 -0.2789 0.05614 0.05390 -0.0535 0.9829 0.0299
-6.000 -0.2353 0.04727 0.04458 -0.0648 0.9719 0.0327
-5.750 -0.2230 0.04170 0.03891 -0.0665 0.9591 0.0336
-5.500 -0.2063 0.04003 0.03718 -0.0658 0.9442 0.0341
-5.250 -0.1888 0.03842 0.03549 -0.0651 0.9278 0.0350
-5.000 -0.1682 0.03623 0.03317 -0.0649 0.9091 0.0366
-4.750 -0.1428 0.02998 0.02625 -0.0660 0.8914 0.0412
-4.500 -0.1224 0.02855 0.02474 -0.0653 0.8698 0.0419
-4.250 -0.0999 0.02736 0.02341 -0.0648 0.8486 0.0429
-4.000 -0.0757 0.02603 0.02187 -0.0644 0.8272 0.0449
-3.750 -0.0492 0.02338 0.01867 -0.0642 0.8075 0.0510
-3.500 -0.0240 0.02241 0.01762 -0.0642 0.7851 0.0524
-3.250 0.0024 0.02151 0.01654 -0.0640 0.7601 0.0551
-2.500 0.0887 0.01399 0.00732 -0.0626 0.6799 0.0415
-2.250 0.1171 0.01368 0.00680 -0.0623 0.6606 0.0406
-2.000 0.1454 0.01325 0.00622 -0.0622 0.6451 0.0403
-1.750 0.1735 0.01259 0.00541 -0.0621 0.6323 0.0402
-1.500 0.2016 0.01206 0.00476 -0.0620 0.6208 0.0402
-1.250 0.2297 0.01150 0.00413 -0.0619 0.6087 0.0404
-1.000 0.2577 0.01097 0.00354 -0.0619 0.5958 0.0409
-0.750 0.2858 0.01057 0.00309 -0.0618 0.5841 0.0421
-0.500 0.3142 0.01034 0.00281 -0.0618 0.5719 0.0430
-0.250 0.3427 0.01016 0.00258 -0.0618 0.5578 0.0441
0.000 0.3713 0.01003 0.00240 -0.0619 0.5411 0.0455
0.250 0.3998 0.00994 0.00224 -0.0619 0.5197 0.0474
1.000 0.4841 0.00982 0.00206 -0.0620 0.4422 0.1366
1.250 0.5099 0.00777 0.00218 -0.0620 0.4231 1.0000
1.500 0.5375 0.00798 0.00221 -0.0620 0.4045 1.0000
1.750 0.5652 0.00818 0.00227 -0.0619 0.3876 1.0000
2.250 0.6208 0.00852 0.00240 -0.0619 0.3598 1.0000
2.500 0.6486 0.00870 0.00247 -0.0619 0.3456 1.0000
2.750 0.6763 0.00888 0.00256 -0.0619 0.3321 1.0000
3.000 0.7041 0.00905 0.00266 -0.0619 0.3207 1.0000
3.250 0.7318 0.00923 0.00276 -0.0618 0.3094 1.0000
3.500 0.7594 0.00942 0.00287 -0.0618 0.2972 1.0000
3.750 0.7870 0.00960 0.00300 -0.0618 0.2850 1.0000
4.000 0.8144 0.00981 0.00314 -0.0618 0.2710 1.0000
4.250 0.8415 0.01007 0.00329 -0.0618 0.2536 1.0000
4.500 0.8680 0.01041 0.00349 -0.0617 0.2264 1.0000
4.750 0.8921 0.01115 0.00388 -0.0614 0.1612 1.0000
5.000 0.9174 0.01168 0.00424 -0.0612 0.1382 1.0000
5.250 0.9439 0.01199 0.00452 -0.0611 0.1331 1.0000
5.500 0.9704 0.01228 0.00480 -0.0609 0.1288 1.0000
5.750 0.9970 0.01253 0.00506 -0.0608 0.1265 1.0000
6.000 1.0236 0.01278 0.00533 -0.0607 0.1246 1.0000
6.250 1.0499 0.01306 0.00562 -0.0606 0.1226 1.0000
6.500 1.0759 0.01336 0.00595 -0.0604 0.1205 1.0000
6.750 1.1011 0.01376 0.00634 -0.0601 0.1163 1.0000
7.000 1.1268 0.01407 0.00667 -0.0599 0.1131 1.0000
7.250 1.1530 0.01430 0.00696 -0.0598 0.1106 1.0000
7.500 1.1786 0.01459 0.00728 -0.0596 0.1074 1.0000
7.750 1.2032 0.01499 0.00768 -0.0593 0.1033 1.0000
8.000 1.2284 0.01531 0.00802 -0.0590 0.0997 1.0000
8.250 1.2546 0.01548 0.00826 -0.0588 0.0958 1.0000
8.500 1.2794 0.01581 0.00857 -0.0585 0.0881 1.0000
8.750 1.3027 0.01630 0.00893 -0.0581 0.0662 1.0000
9.000 1.3247 0.01691 0.00950 -0.0575 0.0601 1.0000
9.250 1.3471 0.01744 0.01010 -0.0569 0.0570 1.0000
9.500 1.3674 0.01816 0.01088 -0.0560 0.0535 1.0000
9.750 1.3863 0.01899 0.01175 -0.0550 0.0493 1.0000
10.000 1.4088 0.01939 0.01226 -0.0544 0.0459 1.0000
10.250 1.4266 0.02022 0.01312 -0.0532 0.0404 1.0000
10.500 1.4486 0.02061 0.01351 -0.0526 0.0322 1.0000
11.000 1.4776 0.02255 0.01535 -0.0494 0.0191 1.0000
11.250 1.4879 0.02369 0.01656 -0.0473 0.0176 1.0000
11.500 1.4948 0.02479 0.01776 -0.0446 0.0167 1.0000
11.750 1.5012 0.02599 0.01907 -0.0422 0.0161 1.0000
12.000 1.5060 0.02740 0.02060 -0.0399 0.0155 1.0000
12.250 1.5090 0.02908 0.02239 -0.0379 0.0151 1.0000
12.500 1.5098 0.03110 0.02453 -0.0362 0.0147 1.0000
12.750 1.5078 0.03361 0.02716 -0.0349 0.0143 1.0000
13.000 1.5025 0.03670 0.03038 -0.0341 0.0140 1.0000
13.250 1.4943 0.04041 0.03422 -0.0338 0.0137 1.0000
13.500 1.4837 0.04477 0.03873 -0.0343 0.0135 1.0000
13.750 1.4794 0.04855 0.04264 -0.0349 0.0134 1.0000
14.000 1.4749 0.05241 0.04663 -0.0356 0.0133 1.0000
14.250 1.4684 0.05654 0.05088 -0.0364 0.0131 1.0000
14.500 1.4607 0.06085 0.05531 -0.0373 0.0130 1.0000
14.750 1.4523 0.06532 0.05990 -0.0383 0.0129 1.0000
15.000 1.4434 0.06993 0.06462 -0.0393 0.0127 1.0000
15.250 1.4350 0.07460 0.06940 -0.0405 0.0126 1.0000
15.500 1.4266 0.07935 0.07426 -0.0418 0.0124 1.0000
15.750 1.4186 0.08408 0.07910 -0.0432 0.0123 1.0000
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Polar data table (+)
Polar graphs
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