GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 422 AIRFOIL (goe422-il) Reynolds number: 500,000 Max Cl/Cd: 85.32 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe422-il-500000-n5.txt Download as CSV file: xf-goe422-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 422 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4487 0.03364 0.02930 -0.1497 0.8325 0.0269
-11.750 -0.4500 0.03082 0.02616 -0.1505 0.8223 0.0270
-11.500 -0.4420 0.02878 0.02384 -0.1507 0.8140 0.0271
-11.250 -0.4292 0.02716 0.02197 -0.1506 0.8074 0.0271
-11.000 -0.4138 0.02569 0.02031 -0.1503 0.8012 0.0273
-10.750 -0.3968 0.02438 0.01883 -0.1500 0.7951 0.0274
-10.500 -0.3772 0.02336 0.01766 -0.1497 0.7897 0.0276
-10.250 -0.3559 0.02246 0.01667 -0.1494 0.7846 0.0277
-10.000 -0.3338 0.02167 0.01578 -0.1491 0.7792 0.0279
-9.750 -0.3111 0.02096 0.01496 -0.1488 0.7742 0.0281
-9.500 -0.2877 0.02030 0.01418 -0.1485 0.7698 0.0282
-9.250 -0.2637 0.01964 0.01345 -0.1483 0.7657 0.0284
-9.000 -0.2393 0.01904 0.01276 -0.1481 0.7612 0.0287
-8.750 -0.2146 0.01849 0.01212 -0.1478 0.7566 0.0289
-8.500 -0.1896 0.01798 0.01150 -0.1476 0.7523 0.0292
-8.250 -0.1643 0.01747 0.01089 -0.1474 0.7484 0.0295
-8.000 -0.1387 0.01696 0.01030 -0.1472 0.7441 0.0298
-7.750 -0.1130 0.01647 0.00973 -0.1469 0.7396 0.0301
-7.500 -0.0871 0.01602 0.00918 -0.1467 0.7353 0.0303
-7.250 -0.0610 0.01561 0.00868 -0.1464 0.7310 0.0306
-7.000 -0.0346 0.01523 0.00822 -0.1462 0.7269 0.0308
-6.750 -0.0082 0.01484 0.00778 -0.1460 0.7222 0.0310
-6.500 0.0178 0.01440 0.00732 -0.1458 0.7177 0.0313
-6.250 0.0441 0.01407 0.00694 -0.1456 0.7131 0.0317
-6.000 0.0709 0.01377 0.00661 -0.1454 0.7086 0.0320
-5.750 0.0978 0.01349 0.00631 -0.1452 0.7037 0.0324
-5.500 0.1247 0.01323 0.00602 -0.1450 0.6986 0.0329
-5.250 0.1515 0.01300 0.00573 -0.1448 0.6936 0.0333
-5.000 0.1786 0.01278 0.00547 -0.1446 0.6887 0.0338
-4.750 0.2056 0.01256 0.00522 -0.1444 0.6822 0.0343
-4.500 0.2321 0.01239 0.00498 -0.1441 0.6749 0.0349
-4.250 0.2585 0.01218 0.00474 -0.1438 0.6667 0.0356
-4.000 0.2846 0.01202 0.00454 -0.1434 0.6570 0.0364
-3.750 0.3112 0.01189 0.00437 -0.1431 0.6485 0.0374
-3.500 0.3377 0.01177 0.00421 -0.1428 0.6399 0.0384
-3.250 0.3643 0.01167 0.00405 -0.1425 0.6328 0.0393
-3.000 0.3911 0.01153 0.00391 -0.1422 0.6253 0.0407
-2.750 0.4173 0.01145 0.00379 -0.1418 0.6181 0.0423
-2.500 0.4443 0.01137 0.00368 -0.1416 0.6106 0.0444
-2.250 0.4703 0.01130 0.00359 -0.1412 0.6019 0.0474
-2.000 0.4966 0.01123 0.00352 -0.1409 0.5937 0.0519
-1.750 0.5225 0.01119 0.00347 -0.1405 0.5848 0.0592
-1.500 0.5484 0.01116 0.00345 -0.1401 0.5772 0.0692
-1.250 0.5747 0.01115 0.00346 -0.1398 0.5690 0.0794
-1.000 0.6001 0.01119 0.00347 -0.1393 0.5613 0.0873
-0.750 0.6265 0.01120 0.00347 -0.1390 0.5534 0.0937
-0.500 0.6515 0.01127 0.00349 -0.1384 0.5449 0.0997
-0.250 0.6773 0.01129 0.00351 -0.1380 0.5369 0.1056
0.000 0.7017 0.01136 0.00354 -0.1373 0.5271 0.1117
0.250 0.7265 0.01141 0.00358 -0.1368 0.5175 0.1194
0.500 0.7500 0.01148 0.00363 -0.1360 0.5074 0.1332
0.750 0.7746 0.01141 0.00371 -0.1355 0.4985 0.1817
1.000 0.7981 0.01136 0.00383 -0.1349 0.4898 0.2580
1.250 0.8226 0.01137 0.00393 -0.1343 0.4824 0.3066
1.500 0.8463 0.01135 0.00405 -0.1337 0.4736 0.3713
1.750 0.8689 0.01129 0.00421 -0.1329 0.4645 0.4680
2.000 0.8892 0.01115 0.00440 -0.1317 0.4530 0.6092
2.250 0.9075 0.01102 0.00468 -0.1298 0.4418 0.7793
2.500 0.9269 0.01119 0.00487 -0.1282 0.4308 0.8166
2.750 0.9468 0.01128 0.00506 -0.1266 0.4204 0.8619
3.000 0.9744 0.01142 0.00526 -0.1266 0.4102 1.0000
3.250 0.9952 0.01170 0.00546 -0.1254 0.4005 1.0000
3.500 1.0161 0.01199 0.00568 -0.1243 0.3920 1.0000
3.750 1.0367 0.01229 0.00592 -0.1232 0.3830 1.0000
4.000 1.0573 0.01261 0.00618 -0.1221 0.3754 1.0000
4.250 1.0783 0.01293 0.00643 -0.1210 0.3675 1.0000
4.500 1.0979 0.01330 0.00675 -0.1198 0.3605 1.0000
4.750 1.1193 0.01361 0.00702 -0.1189 0.3542 1.0000
5.000 1.1395 0.01398 0.00734 -0.1178 0.3478 1.0000
5.250 1.1590 0.01438 0.00770 -0.1167 0.3421 1.0000
5.500 1.1799 0.01472 0.00802 -0.1157 0.3365 1.0000
5.750 1.1992 0.01515 0.00841 -0.1146 0.3303 1.0000
6.000 1.2176 0.01562 0.00884 -0.1134 0.3247 1.0000
6.250 1.2380 0.01601 0.00922 -0.1124 0.3196 1.0000
6.500 1.2566 0.01649 0.00967 -0.1113 0.3136 1.0000
6.750 1.2741 0.01704 0.01018 -0.1100 0.3088 1.0000
7.000 1.2940 0.01747 0.01062 -0.1091 0.3053 1.0000
7.250 1.3138 0.01792 0.01107 -0.1083 0.3013 1.0000
7.500 1.3320 0.01846 0.01160 -0.1072 0.2971 1.0000
7.750 1.3488 0.01907 0.01221 -0.1060 0.2928 1.0000
8.000 1.3667 0.01965 0.01279 -0.1050 0.2892 1.0000
8.250 1.3855 0.02019 0.01334 -0.1041 0.2852 1.0000
8.500 1.4030 0.02082 0.01398 -0.1031 0.2806 1.0000
8.750 1.4182 0.02158 0.01473 -0.1019 0.2759 1.0000
9.000 1.4349 0.02228 0.01543 -0.1009 0.2717 1.0000
9.250 1.4516 0.02299 0.01616 -0.0999 0.2663 1.0000
9.500 1.4654 0.02390 0.01706 -0.0987 0.2599 1.0000
9.750 1.4799 0.02479 0.01795 -0.0975 0.2532 1.0000
10.000 1.4901 0.02597 0.01909 -0.0961 0.2424 1.0000
10.250 1.5005 0.02718 0.02026 -0.0947 0.2300 1.0000
10.500 1.5061 0.02877 0.02178 -0.0929 0.2132 1.0000
10.750 1.4883 0.03218 0.02490 -0.0892 0.1685 1.0000
11.000 1.4653 0.03619 0.02866 -0.0854 0.1255 1.0000
11.250 1.4546 0.03938 0.03172 -0.0829 0.0999 1.0000
11.500 1.4563 0.04161 0.03394 -0.0815 0.0927 1.0000
11.750 1.4628 0.04346 0.03582 -0.0804 0.0904 1.0000
12.000 1.4692 0.04536 0.03775 -0.0795 0.0884 1.0000
12.250 1.4747 0.04740 0.03982 -0.0785 0.0868 1.0000
12.500 1.4804 0.04943 0.04190 -0.0777 0.0854 1.0000
12.750 1.4852 0.05160 0.04412 -0.0768 0.0843 1.0000
13.000 1.4907 0.05372 0.04629 -0.0761 0.0835 1.0000
13.250 1.4966 0.05586 0.04850 -0.0755 0.0830 1.0000
13.500 1.5015 0.05812 0.05082 -0.0749 0.0825 1.0000
13.750 1.5059 0.06045 0.05323 -0.0743 0.0821 1.0000
14.000 1.5089 0.06297 0.05582 -0.0738 0.0816 1.0000
14.250 1.5119 0.06551 0.05843 -0.0733 0.0812 1.0000
14.500 1.5136 0.06827 0.06126 -0.0729 0.0808 1.0000
14.750 1.5147 0.07111 0.06418 -0.0725 0.0804 1.0000
15.000 1.5153 0.07403 0.06717 -0.0722 0.0800 1.0000
15.250 1.5142 0.07717 0.07040 -0.0719 0.0797 1.0000
15.500 1.5130 0.08037 0.07368 -0.0717 0.0793 1.0000
15.750 1.5116 0.08362 0.07700 -0.0715 0.0790 1.0000
16.000 1.5088 0.08709 0.08056 -0.0715 0.0786 1.0000
16.250 1.5062 0.09053 0.08407 -0.0715 0.0783 1.0000
16.500 1.5031 0.09405 0.08767 -0.0716 0.0780 1.0000
16.750 1.4996 0.09768 0.09138 -0.0718 0.0777 1.0000
17.000 1.4967 0.10121 0.09498 -0.0720 0.0774 1.0000
17.250 1.4927 0.10494 0.09878 -0.0723 0.0770 1.0000
17.500 1.4897 0.10854 0.10245 -0.0727 0.0766 1.0000
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Polar data table (+)
Polar graphs
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