GOE 620 AIRFOIL (goe620-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 620 AIRFOIL (goe620-il) Reynolds number: 500,000 Max Cl/Cd: 97.7 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe620-il-500000.txt Download as CSV file: xf-goe620-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 620 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4995 0.05094 0.04740 -0.1421 0.9696 0.0415
-13.500 -0.5175 0.04284 0.03901 -0.1535 0.9618 0.0415
-13.250 -0.5214 0.03635 0.03218 -0.1647 0.9541 0.0418
-13.000 -0.5034 0.03341 0.02914 -0.1692 0.9473 0.0423
-12.750 -0.4818 0.03134 0.02696 -0.1726 0.9396 0.0427
-12.500 -0.4627 0.02992 0.02544 -0.1741 0.9296 0.0431
-12.250 -0.4421 0.02855 0.02395 -0.1754 0.9202 0.0435
-12.000 -0.4342 0.02752 0.02278 -0.1738 0.9066 0.0439
-11.750 -0.4241 0.02641 0.02151 -0.1725 0.8945 0.0443
-11.500 -0.4100 0.02536 0.02028 -0.1716 0.8844 0.0448
-11.250 -0.4016 0.02445 0.01921 -0.1693 0.8733 0.0451
-11.000 -0.3866 0.02354 0.01810 -0.1680 0.8650 0.0456
-10.750 -0.3745 0.02279 0.01719 -0.1660 0.8557 0.0460
-10.500 -0.3570 0.02211 0.01630 -0.1648 0.8484 0.0464
-10.250 -0.3426 0.02138 0.01543 -0.1630 0.8408 0.0469
-10.000 -0.3234 0.02024 0.01426 -0.1621 0.8343 0.0476
-9.750 -0.3012 0.01962 0.01358 -0.1615 0.8286 0.0482
-9.500 -0.2823 0.01911 0.01304 -0.1601 0.8222 0.0489
-9.250 -0.2615 0.01859 0.01245 -0.1591 0.8162 0.0495
-9.000 -0.2382 0.01810 0.01183 -0.1585 0.8107 0.0502
-8.750 -0.2183 0.01762 0.01129 -0.1571 0.8051 0.0509
-8.500 -0.1966 0.01716 0.01076 -0.1561 0.7998 0.0515
-8.250 -0.1729 0.01681 0.01028 -0.1554 0.7951 0.0521
-8.000 -0.1510 0.01611 0.00951 -0.1546 0.7907 0.0530
-7.750 -0.1303 0.01556 0.00899 -0.1534 0.7860 0.0539
-7.500 -0.1075 0.01519 0.00861 -0.1525 0.7815 0.0549
-7.250 -0.0834 0.01485 0.00822 -0.1519 0.7773 0.0560
-7.000 -0.0579 0.01456 0.00784 -0.1514 0.7732 0.0571
-6.750 -0.0354 0.01426 0.00751 -0.1504 0.7691 0.0580
-6.500 -0.0128 0.01387 0.00708 -0.1494 0.7648 0.0590
-6.250 0.0096 0.01342 0.00663 -0.1484 0.7607 0.0603
-6.000 0.0348 0.01314 0.00630 -0.1479 0.7569 0.0618
-5.750 0.0597 0.01292 0.00605 -0.1473 0.7530 0.0634
-5.500 0.0836 0.01271 0.00582 -0.1465 0.7488 0.0650
-5.250 0.1065 0.01235 0.00546 -0.1455 0.7447 0.0671
-5.000 0.1315 0.01211 0.00520 -0.1449 0.7407 0.0694
-4.750 0.1588 0.01196 0.00498 -0.1447 0.7366 0.0719
-4.500 0.1823 0.01172 0.00476 -0.1438 0.7328 0.0752
-4.250 0.2067 0.01153 0.00459 -0.1430 0.7286 0.0798
-4.000 0.2315 0.01131 0.00439 -0.1423 0.7242 0.0874
-3.750 0.2573 0.01107 0.00420 -0.1418 0.7201 0.1032
-3.500 0.2828 0.01083 0.00406 -0.1414 0.7161 0.1320
-3.250 0.3059 0.01063 0.00398 -0.1404 0.7116 0.1592
-3.000 0.3311 0.01051 0.00391 -0.1397 0.7069 0.1811
-2.750 0.3575 0.01043 0.00384 -0.1393 0.7025 0.1984
-2.500 0.3854 0.01040 0.00380 -0.1393 0.6981 0.2140
-2.250 0.4086 0.01030 0.00377 -0.1382 0.6933 0.2275
-2.000 0.4334 0.01022 0.00372 -0.1374 0.6881 0.2408
-1.750 0.4598 0.01018 0.00366 -0.1370 0.6833 0.2547
-1.500 0.4861 0.01015 0.00365 -0.1366 0.6785 0.2692
-1.250 0.5091 0.01007 0.00363 -0.1355 0.6729 0.2833
-1.000 0.5336 0.01001 0.00359 -0.1347 0.6672 0.2976
-0.750 0.5607 0.01002 0.00355 -0.1344 0.6617 0.3128
-0.500 0.5819 0.00994 0.00355 -0.1329 0.6551 0.3290
-0.250 0.6048 0.00987 0.00351 -0.1318 0.6478 0.3462
0.000 0.6278 0.00984 0.00350 -0.1306 0.6406 0.3648
0.250 0.6489 0.00978 0.00349 -0.1291 0.6321 0.3840
0.500 0.6707 0.00976 0.00347 -0.1278 0.6240 0.4043
0.750 0.6903 0.00972 0.00347 -0.1260 0.6142 0.4248
1.000 0.7099 0.00970 0.00348 -0.1242 0.6047 0.4486
1.250 0.7288 0.00967 0.00352 -0.1223 0.5954 0.4783
1.500 0.7480 0.00967 0.00357 -0.1204 0.5875 0.5129
1.750 0.7648 0.00964 0.00364 -0.1181 0.5791 0.5496
2.000 0.7815 0.00966 0.00370 -0.1157 0.5714 0.5872
2.250 0.7974 0.00963 0.00379 -0.1132 0.5629 0.6304
2.500 0.8106 0.00961 0.00391 -0.1101 0.5545 0.6938
2.750 0.9403 0.00963 0.00446 -0.1321 0.5396 1.0000
3.000 0.9545 0.00977 0.00455 -0.1293 0.5318 1.0000
3.250 0.9685 0.00994 0.00465 -0.1264 0.5235 1.0000
3.500 0.9838 0.01012 0.00477 -0.1239 0.5160 1.0000
3.750 0.9995 0.01029 0.00490 -0.1215 0.5079 1.0000
4.000 1.0151 0.01052 0.00505 -0.1191 0.5005 1.0000
4.250 1.0332 0.01069 0.00521 -0.1172 0.4934 1.0000
4.500 1.0491 0.01093 0.00538 -0.1149 0.4857 1.0000
4.750 1.0672 0.01114 0.00557 -0.1131 0.4789 1.0000
5.000 1.0844 0.01137 0.00578 -0.1111 0.4713 1.0000
5.250 1.1008 0.01166 0.00601 -0.1091 0.4643 1.0000
5.500 1.1194 0.01189 0.00623 -0.1075 0.4569 1.0000
5.750 1.1351 0.01221 0.00650 -0.1054 0.4492 1.0000
6.000 1.1535 0.01248 0.00676 -0.1038 0.4420 1.0000
6.250 1.1696 0.01282 0.00707 -0.1019 0.4338 1.0000
6.500 1.1860 0.01318 0.00740 -0.1001 0.4257 1.0000
6.750 1.2021 0.01356 0.00775 -0.0982 0.4169 1.0000
7.000 1.2178 0.01398 0.00814 -0.0964 0.4090 1.0000
7.250 1.2343 0.01439 0.00854 -0.0948 0.4002 1.0000
7.500 1.2489 0.01490 0.00901 -0.0929 0.3919 1.0000
7.750 1.2649 0.01537 0.00947 -0.0913 0.3828 1.0000
8.000 1.2787 0.01595 0.01002 -0.0894 0.3736 1.0000
8.250 1.2926 0.01656 0.01060 -0.0876 0.3635 1.0000
8.500 1.3067 0.01719 0.01120 -0.0859 0.3543 1.0000
8.750 1.3196 0.01789 0.01187 -0.0841 0.3452 1.0000
9.000 1.3337 0.01857 0.01254 -0.0825 0.3364 1.0000
9.250 1.3452 0.01941 0.01334 -0.0807 0.3274 1.0000
9.500 1.3590 0.02015 0.01408 -0.0793 0.3188 1.0000
9.750 1.3698 0.02108 0.01497 -0.0775 0.3104 1.0000
10.000 1.3833 0.02189 0.01578 -0.0761 0.3026 1.0000
10.250 1.3943 0.02286 0.01673 -0.0745 0.2951 1.0000
10.500 1.4068 0.02377 0.01764 -0.0731 0.2885 1.0000
10.750 1.4190 0.02472 0.01859 -0.0717 0.2817 1.0000
11.000 1.4281 0.02589 0.01972 -0.0701 0.2755 1.0000
11.250 1.4428 0.02673 0.02061 -0.0691 0.2703 1.0000
11.500 1.4544 0.02778 0.02167 -0.0679 0.2651 1.0000
11.750 1.4629 0.02906 0.02293 -0.0664 0.2596 1.0000
12.000 1.4764 0.03002 0.02394 -0.0654 0.2539 1.0000
12.250 1.4874 0.03117 0.02510 -0.0643 0.2489 1.0000
12.500 1.4941 0.03266 0.02658 -0.0628 0.2433 1.0000
12.750 1.5080 0.03364 0.02762 -0.0620 0.2387 1.0000
13.000 1.5166 0.03505 0.02903 -0.0608 0.2326 1.0000
13.250 1.5231 0.03662 0.03061 -0.0596 0.2265 1.0000
13.500 1.5326 0.03801 0.03204 -0.0586 0.2194 1.0000
13.750 1.5356 0.03995 0.03394 -0.0573 0.2115 1.0000
14.000 1.5431 0.04157 0.03559 -0.0563 0.2024 1.0000
14.250 1.5466 0.04354 0.03755 -0.0552 0.1926 1.0000
14.500 1.5468 0.04586 0.03985 -0.0540 0.1810 1.0000
14.750 1.5454 0.04838 0.04233 -0.0528 0.1674 1.0000
15.000 1.5426 0.05110 0.04500 -0.0517 0.1556 1.0000
15.250 1.5400 0.05383 0.04770 -0.0507 0.1477 1.0000
15.500 1.5359 0.05678 0.05065 -0.0498 0.1419 1.0000
15.750 1.5373 0.05922 0.05312 -0.0491 0.1389 1.0000
16.000 1.5370 0.06187 0.05581 -0.0484 0.1359 1.0000
16.250 1.5355 0.06470 0.05867 -0.0478 0.1337 1.0000
16.500 1.5324 0.06770 0.06169 -0.0473 0.1310 1.0000
16.750 1.5349 0.07014 0.06420 -0.0469 0.1294 1.0000
17.000 1.5385 0.07246 0.06660 -0.0466 0.1279 1.0000
17.250 1.5398 0.07509 0.06929 -0.0463 0.1260 1.0000
17.500 1.5399 0.07784 0.07210 -0.0461 0.1242 1.0000
17.750 1.5394 0.08067 0.07497 -0.0459 0.1228 1.0000
18.000 1.5371 0.08372 0.07805 -0.0457 0.1209 1.0000
18.250 1.5362 0.08657 0.08092 -0.0456 0.1189 1.0000
18.500 1.5395 0.08899 0.08341 -0.0456 0.1177 1.0000
18.750 1.5421 0.09157 0.08609 -0.0457 0.1165 1.0000
19.000 1.5453 0.09403 0.08863 -0.0458 0.1152 1.0000
19.250 1.5461 0.09682 0.09150 -0.0460 0.1136 1.0000
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Polar data table (+)
Polar graphs
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