GOE 418 AIRFOIL (goe418-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 418 AIRFOIL (goe418-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.7 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe418-il-1000000.txt Download as CSV file: xf-goe418-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 418 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -1.0893 0.03216 0.02911 -0.1028 1.0000 0.0379
-14.750 -1.0905 0.02968 0.02649 -0.1017 1.0000 0.0382
-14.500 -1.0853 0.02806 0.02476 -0.1001 1.0000 0.0385
-14.250 -1.0790 0.02669 0.02330 -0.0981 1.0000 0.0389
-14.000 -1.0717 0.02559 0.02210 -0.0958 1.0000 0.0392
-13.750 -1.0414 0.02431 0.02068 -0.0977 0.9984 0.0397
-13.500 -1.0101 0.02322 0.01945 -0.0995 0.9962 0.0400
-13.250 -0.9807 0.02167 0.01777 -0.1015 0.9936 0.0406
-13.000 -0.9521 0.02061 0.01665 -0.1026 0.9907 0.0411
-12.750 -0.9225 0.01984 0.01585 -0.1035 0.9875 0.0416
-12.500 -0.8909 0.01920 0.01516 -0.1047 0.9847 0.0421
-12.250 -0.8583 0.01854 0.01444 -0.1060 0.9825 0.0427
-12.000 -0.8254 0.01795 0.01378 -0.1072 0.9804 0.0433
-11.750 -0.7980 0.01739 0.01314 -0.1073 0.9747 0.0439
-11.500 -0.7660 0.01684 0.01249 -0.1083 0.9712 0.0444
-11.250 -0.7323 0.01608 0.01164 -0.1098 0.9685 0.0449
-11.000 -0.7031 0.01530 0.01082 -0.1104 0.9619 0.0457
-10.750 -0.6698 0.01479 0.01028 -0.1116 0.9562 0.0463
-10.500 -0.6364 0.01437 0.00982 -0.1127 0.9498 0.0470
-10.250 -0.6053 0.01397 0.00936 -0.1133 0.9411 0.0477
-10.000 -0.5751 0.01362 0.00893 -0.1136 0.9320 0.0484
-9.750 -0.5462 0.01333 0.00854 -0.1136 0.9216 0.0491
-9.500 -0.5196 0.01302 0.00814 -0.1131 0.9112 0.0496
-9.250 -0.4949 0.01246 0.00750 -0.1125 0.9006 0.0506
-9.000 -0.4694 0.01215 0.00716 -0.1118 0.8907 0.0513
-8.750 -0.4431 0.01191 0.00686 -0.1113 0.8813 0.0521
-8.500 -0.4170 0.01167 0.00656 -0.1106 0.8714 0.0529
-8.250 -0.3907 0.01145 0.00626 -0.1100 0.8613 0.0537
-8.000 -0.3642 0.01127 0.00600 -0.1094 0.8501 0.0544
-7.750 -0.3389 0.01093 0.00559 -0.1087 0.8384 0.0554
-7.500 -0.3133 0.01067 0.00528 -0.1079 0.8249 0.0565
-7.250 -0.2869 0.01048 0.00505 -0.1073 0.8109 0.0575
-7.000 -0.2607 0.01033 0.00482 -0.1066 0.7955 0.0585
-6.750 -0.2345 0.01019 0.00459 -0.1059 0.7776 0.0595
-6.500 -0.2084 0.01010 0.00438 -0.1052 0.7570 0.0603
-6.250 -0.1835 0.00987 0.00407 -0.1043 0.7342 0.0618
-6.000 -0.1578 0.00979 0.00390 -0.1036 0.7116 0.0632
-5.750 -0.1316 0.00973 0.00376 -0.1029 0.6921 0.0645
-5.500 -0.1050 0.00967 0.00361 -0.1023 0.6761 0.0658
-5.250 -0.0785 0.00956 0.00342 -0.1017 0.6628 0.0671
-4.750 -0.0246 0.00941 0.00320 -0.1007 0.6400 0.0707
-4.500 0.0024 0.00940 0.00312 -0.1001 0.6291 0.0724
-4.250 0.0298 0.00929 0.00297 -0.0997 0.6200 0.0742
-4.000 0.0568 0.00925 0.00291 -0.0992 0.6111 0.0762
-3.750 0.0849 0.00922 0.00287 -0.0989 0.6049 0.0783
-3.500 0.1129 0.00921 0.00283 -0.0986 0.5987 0.0801
-3.250 0.1400 0.00913 0.00273 -0.0981 0.5923 0.0825
-3.000 0.1681 0.00911 0.00272 -0.0978 0.5873 0.0845
-2.750 0.1962 0.00909 0.00270 -0.0975 0.5813 0.0866
-2.500 0.2239 0.00913 0.00268 -0.0971 0.5738 0.0883
-2.250 0.2513 0.00903 0.00257 -0.0967 0.5685 0.0906
-2.000 0.2794 0.00898 0.00255 -0.0964 0.5636 0.0927
-1.750 0.3073 0.00898 0.00254 -0.0961 0.5582 0.0947
-1.250 0.3630 0.00900 0.00251 -0.0954 0.5455 0.0979
-1.000 0.3901 0.00886 0.00236 -0.0950 0.5394 0.1005
-0.750 0.4172 0.00885 0.00234 -0.0945 0.5332 0.1025
-0.500 0.4452 0.00881 0.00232 -0.0942 0.5286 0.1043
-0.250 0.4731 0.00879 0.00230 -0.0939 0.5232 0.1063
0.000 0.5006 0.00881 0.00230 -0.0935 0.5172 0.1078
0.250 0.5281 0.00882 0.00229 -0.0932 0.5114 0.1089
0.500 0.5552 0.00868 0.00217 -0.0927 0.5052 0.1120
0.750 0.5822 0.00868 0.00215 -0.0923 0.4977 0.1142
1.000 0.6096 0.00867 0.00215 -0.0919 0.4905 0.1162
1.250 0.6369 0.00868 0.00215 -0.0915 0.4826 0.1183
1.500 0.6637 0.00873 0.00216 -0.0911 0.4748 0.1200
1.750 0.6911 0.00872 0.00216 -0.0907 0.4666 0.1217
2.000 0.7174 0.00874 0.00215 -0.0901 0.4571 0.1251
2.250 0.7442 0.00875 0.00217 -0.0897 0.4463 0.1284
2.500 0.7705 0.00882 0.00221 -0.0892 0.4338 0.1313
2.750 0.7964 0.00893 0.00226 -0.0886 0.4190 0.1339
3.000 0.8218 0.00903 0.00232 -0.0879 0.4025 0.1401
3.250 0.8470 0.00916 0.00241 -0.0872 0.3871 0.1481
3.500 0.8721 0.00924 0.00251 -0.0865 0.3722 0.1742
3.750 0.8962 0.00923 0.00268 -0.0857 0.3580 0.2696
4.000 0.9202 0.00924 0.00284 -0.0849 0.3451 0.3533
4.250 0.9757 0.00829 0.00323 -0.0913 0.3270 1.0000
4.500 0.9989 0.00851 0.00338 -0.0902 0.3153 1.0000
4.750 1.0221 0.00875 0.00353 -0.0891 0.3024 1.0000
5.000 1.0457 0.00896 0.00368 -0.0882 0.2907 1.0000
5.250 1.0687 0.00920 0.00386 -0.0871 0.2776 1.0000
5.500 1.0910 0.00950 0.00405 -0.0859 0.2605 1.0000
5.750 1.1109 0.00992 0.00432 -0.0844 0.2345 1.0000
6.000 1.1251 0.01068 0.00477 -0.0819 0.1846 1.0000
6.250 1.1390 0.01143 0.00528 -0.0794 0.1482 1.0000
6.500 1.1588 0.01182 0.00560 -0.0779 0.1385 1.0000
6.750 1.1794 0.01216 0.00590 -0.0765 0.1324 1.0000
7.000 1.2008 0.01243 0.00615 -0.0753 0.1293 1.0000
7.250 1.2218 0.01272 0.00643 -0.0739 0.1270 1.0000
7.500 1.2420 0.01303 0.00672 -0.0725 0.1247 1.0000
7.750 1.2614 0.01336 0.00705 -0.0709 0.1225 1.0000
8.000 1.2799 0.01369 0.00738 -0.0692 0.1205 1.0000
8.250 1.2986 0.01393 0.00764 -0.0675 0.1197 1.0000
8.500 1.3165 0.01419 0.00792 -0.0656 0.1187 1.0000
8.750 1.3338 0.01448 0.00823 -0.0637 0.1178 1.0000
9.000 1.3510 0.01479 0.00856 -0.0618 0.1168 1.0000
9.250 1.3678 0.01514 0.00892 -0.0600 0.1157 1.0000
9.500 1.3840 0.01552 0.00932 -0.0581 0.1145 1.0000
9.750 1.3995 0.01596 0.00977 -0.0561 0.1131 1.0000
10.000 1.4137 0.01646 0.01028 -0.0541 0.1115 1.0000
10.250 1.4264 0.01706 0.01091 -0.0520 0.1099 1.0000
10.500 1.4407 0.01762 0.01149 -0.0501 0.1088 1.0000
10.750 1.4588 0.01800 0.01191 -0.0489 0.1081 1.0000
11.000 1.4756 0.01847 0.01242 -0.0475 0.1072 1.0000
11.250 1.4923 0.01897 0.01294 -0.0462 0.1061 1.0000
11.500 1.5085 0.01951 0.01351 -0.0449 0.1047 1.0000
11.750 1.5237 0.02013 0.01416 -0.0436 0.1034 1.0000
12.000 1.5375 0.02087 0.01491 -0.0422 0.1019 1.0000
12.250 1.5493 0.02176 0.01583 -0.0407 0.1003 1.0000
12.500 1.5580 0.02291 0.01702 -0.0391 0.0985 1.0000
12.750 1.5750 0.02354 0.01769 -0.0382 0.0976 1.0000
13.000 1.5929 0.02411 0.01831 -0.0375 0.0960 1.0000
13.250 1.6089 0.02484 0.01907 -0.0367 0.0941 1.0000
13.500 1.6224 0.02579 0.02003 -0.0358 0.0918 1.0000
13.750 1.6327 0.02701 0.02126 -0.0348 0.0890 1.0000
14.000 1.6481 0.02785 0.02214 -0.0341 0.0864 1.0000
14.250 1.6598 0.02900 0.02329 -0.0333 0.0810 1.0000
14.500 1.6668 0.03061 0.02484 -0.0324 0.0717 1.0000
14.750 1.6616 0.03334 0.02748 -0.0312 0.0586 1.0000
15.000 1.6535 0.03650 0.03062 -0.0303 0.0507 1.0000
15.250 1.6481 0.03953 0.03367 -0.0296 0.0464 1.0000
15.500 1.6460 0.04231 0.03649 -0.0291 0.0439 1.0000
15.750 1.6415 0.04541 0.03963 -0.0287 0.0419 1.0000
16.000 1.6415 0.04808 0.04237 -0.0284 0.0408 1.0000
16.250 1.6402 0.05091 0.04526 -0.0282 0.0398 1.0000
16.500 1.6366 0.05404 0.04846 -0.0281 0.0388 1.0000
16.750 1.6322 0.05733 0.05180 -0.0281 0.0381 1.0000
17.000 1.6251 0.06096 0.05550 -0.0281 0.0373 1.0000
17.250 1.6216 0.06423 0.05885 -0.0283 0.0369 1.0000
17.500 1.6197 0.06735 0.06204 -0.0284 0.0363 1.0000
17.750 1.6159 0.07073 0.06551 -0.0287 0.0360 1.0000
18.000 1.6106 0.07433 0.06919 -0.0291 0.0355 1.0000
18.250 1.6049 0.07804 0.07298 -0.0296 0.0351 1.0000
18.500 1.5983 0.08193 0.07694 -0.0302 0.0347 1.0000
18.750 1.5891 0.08620 0.08128 -0.0310 0.0342 1.0000
19.000 1.5796 0.09061 0.08578 -0.0319 0.0339 1.0000
19.250 1.5685 0.09533 0.09058 -0.0331 0.0335 1.0000
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