GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 422 AIRFOIL (goe422-il) Reynolds number: 100,000 Max Cl/Cd: 47.56 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe422-il-100000-n5.txt Download as CSV file: xf-goe422-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.0102 0.11137 0.10579 -0.1045 0.9267 0.0813
-10.250 0.0085 0.10869 0.10312 -0.1062 0.9162 0.0818
-9.250 0.0258 0.09186 0.08621 -0.1137 0.8872 0.0602
-9.000 0.0361 0.08862 0.08295 -0.1154 0.8820 0.0598
-8.750 0.0398 0.08574 0.08007 -0.1163 0.8736 0.0595
-8.500 0.0462 0.08241 0.07672 -0.1180 0.8674 0.0591
-8.250 0.0493 0.07916 0.07347 -0.1193 0.8602 0.0583
-7.750 0.0128 0.06650 0.06073 -0.1283 0.8420 0.0544
-7.500 0.0138 0.06218 0.05635 -0.1316 0.8347 0.0540
-7.250 0.0158 0.05611 0.05008 -0.1367 0.8297 0.0535
-7.000 0.0057 0.05140 0.04518 -0.1376 0.8198 0.0531
-6.750 0.0071 0.04577 0.03914 -0.1399 0.8139 0.0530
-6.500 0.0146 0.04081 0.03363 -0.1414 0.8090 0.0534
-6.250 0.0155 0.03743 0.02969 -0.1397 0.8002 0.0542
-6.000 0.0376 0.03549 0.02748 -0.1400 0.7954 0.0551
-5.750 0.0663 0.03405 0.02586 -0.1409 0.7919 0.0560
-5.500 0.0824 0.03277 0.02436 -0.1397 0.7851 0.0566
-5.250 0.1017 0.03140 0.02273 -0.1388 0.7786 0.0573
-5.000 0.1290 0.02984 0.02083 -0.1391 0.7742 0.0583
-4.750 0.1605 0.02825 0.01887 -0.1399 0.7708 0.0596
-4.500 0.1761 0.02754 0.01796 -0.1379 0.7630 0.0607
-4.250 0.2006 0.02708 0.01750 -0.1375 0.7569 0.0623
-4.000 0.2315 0.02634 0.01662 -0.1380 0.7527 0.0647
-3.750 0.2627 0.02543 0.01548 -0.1385 0.7486 0.0672
-3.500 0.2777 0.02527 0.01538 -0.1363 0.7401 0.0687
-3.250 0.3058 0.02471 0.01476 -0.1363 0.7347 0.0711
-3.000 0.3388 0.02398 0.01388 -0.1370 0.7308 0.0748
-2.750 0.3567 0.02390 0.01386 -0.1353 0.7228 0.0781
-2.500 0.3822 0.02352 0.01342 -0.1347 0.7163 0.0834
-2.250 0.4148 0.02297 0.01280 -0.1353 0.7116 0.0902
-2.000 0.4334 0.02279 0.01267 -0.1337 0.7030 0.0963
-1.750 0.4603 0.02236 0.01222 -0.1333 0.6957 0.1059
-1.500 0.4900 0.02187 0.01169 -0.1335 0.6895 0.1182
-1.250 0.5086 0.02172 0.01160 -0.1318 0.6801 0.1301
-1.000 0.5391 0.02125 0.01115 -0.1322 0.6742 0.1476
-0.750 0.5594 0.02115 0.01115 -0.1308 0.6659 0.1662
-0.500 0.5851 0.02088 0.01100 -0.1304 0.6588 0.1959
-0.250 0.6153 0.02044 0.01074 -0.1308 0.6532 0.2606
0.000 0.6332 0.02033 0.01093 -0.1292 0.6442 0.3427
0.250 0.6604 0.01972 0.01081 -0.1290 0.6380 0.4985
0.500 0.6752 0.01923 0.01107 -0.1258 0.6305 0.7434
0.750 0.7117 0.01897 0.01102 -0.1266 0.6226 0.9269
1.000 0.7466 0.01893 0.01076 -0.1278 0.6162 1.0000
1.250 0.7642 0.01922 0.01095 -0.1261 0.6071 1.0000
1.500 0.7927 0.01924 0.01078 -0.1261 0.6003 1.0000
1.750 0.8118 0.01952 0.01097 -0.1246 0.5914 1.0000
2.000 0.8370 0.01964 0.01093 -0.1241 0.5836 1.0000
2.250 0.8597 0.01985 0.01103 -0.1232 0.5756 1.0000
2.500 0.8816 0.02008 0.01116 -0.1222 0.5673 1.0000
2.750 0.9087 0.02022 0.01113 -0.1220 0.5604 1.0000
3.000 0.9264 0.02058 0.01145 -0.1204 0.5514 1.0000
3.250 0.9539 0.02070 0.01141 -0.1202 0.5443 1.0000
3.500 0.9703 0.02110 0.01177 -0.1184 0.5352 1.0000
3.750 0.9938 0.02132 0.01187 -0.1177 0.5274 1.0000
4.000 1.0129 0.02167 0.01216 -0.1163 0.5192 1.0000
4.250 1.0327 0.02201 0.01244 -0.1150 0.5110 1.0000
4.500 1.0569 0.02229 0.01259 -0.1145 0.5040 1.0000
4.750 1.0726 0.02279 0.01309 -0.1127 0.4957 1.0000
5.000 1.0968 0.02306 0.01325 -0.1121 0.4888 1.0000
5.250 1.1126 0.02360 0.01377 -0.1104 0.4805 1.0000
5.500 1.1316 0.02402 0.01413 -0.1092 0.4725 1.0000
5.750 1.1498 0.02448 0.01453 -0.1078 0.4646 1.0000
6.000 1.1650 0.02504 0.01507 -0.1061 0.4561 1.0000
6.250 1.1851 0.02545 0.01538 -0.1051 0.4488 1.0000
6.500 1.1977 0.02616 0.01612 -0.1031 0.4406 1.0000
6.750 1.2177 0.02660 0.01647 -0.1022 0.4341 1.0000
7.000 1.2330 0.02728 0.01716 -0.1007 0.4275 1.0000
7.250 1.2484 0.02797 0.01787 -0.0992 0.4214 1.0000
7.500 1.2691 0.02844 0.01827 -0.0985 0.4163 1.0000
7.750 1.2849 0.02916 0.01901 -0.0972 0.4110 1.0000
8.000 1.2982 0.02999 0.01988 -0.0956 0.4051 1.0000
8.250 1.3156 0.03060 0.02046 -0.0945 0.3998 1.0000
8.500 1.3319 0.03130 0.02114 -0.0933 0.3945 1.0000
8.750 1.3417 0.03233 0.02225 -0.0916 0.3885 1.0000
9.000 1.3564 0.03312 0.02305 -0.0903 0.3834 1.0000
9.250 1.3775 0.03359 0.02346 -0.0897 0.3793 1.0000
9.500 1.3865 0.03479 0.02477 -0.0880 0.3748 1.0000
9.750 1.3977 0.03589 0.02595 -0.0866 0.3705 1.0000
10.000 1.4116 0.03683 0.02694 -0.0855 0.3666 1.0000
10.250 1.4303 0.03746 0.02755 -0.0847 0.3630 1.0000
10.500 1.4435 0.03847 0.02861 -0.0836 0.3592 1.0000
10.750 1.4482 0.04005 0.03033 -0.0819 0.3549 1.0000
11.000 1.4570 0.04138 0.03175 -0.0805 0.3508 1.0000
11.250 1.4704 0.04235 0.03275 -0.0795 0.3469 1.0000
11.500 1.4892 0.04294 0.03331 -0.0788 0.3429 1.0000
11.750 1.4842 0.04532 0.03589 -0.0767 0.3382 1.0000
12.000 1.4863 0.04723 0.03792 -0.0751 0.3336 1.0000
12.250 1.4959 0.04852 0.03926 -0.0740 0.3293 1.0000
12.500 1.5134 0.04913 0.03984 -0.0733 0.3252 1.0000
12.750 1.4985 0.05265 0.04359 -0.0713 0.3197 1.0000
13.000 1.4954 0.05518 0.04624 -0.0699 0.3140 1.0000
13.250 1.5100 0.05595 0.04699 -0.0691 0.3088 1.0000
13.500 1.4944 0.05998 0.05122 -0.0677 0.3032 1.0000
13.750 1.4830 0.06373 0.05513 -0.0666 0.2973 1.0000
14.000 1.4933 0.06502 0.05642 -0.0659 0.2918 1.0000
14.250 1.4704 0.07042 0.06204 -0.0651 0.2858 1.0000
14.500 1.4507 0.07568 0.06748 -0.0647 0.2797 1.0000
14.750 1.4627 0.07689 0.06869 -0.0643 0.2747 1.0000
15.000 1.4046 0.08780 0.07993 -0.0648 0.2665 1.0000
15.250 1.4006 0.09136 0.08356 -0.0649 0.2599 1.0000
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Polar data table (+)
Polar graphs
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