GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 406 AIRFOIL (goe406-il) Reynolds number: 500,000 Max Cl/Cd: 94.84 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe406-il-500000.txt Download as CSV file: xf-goe406-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 406 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1497 0.09034 0.08800 -0.0745 0.9756 0.0266
-8.750 -0.1320 0.08558 0.08324 -0.0819 0.9717 0.0267
-8.500 -0.1201 0.08194 0.07961 -0.0825 0.9642 0.0269
-8.250 -0.0986 0.07871 0.07638 -0.0846 0.9594 0.0271
-8.000 -0.0852 0.07596 0.07363 -0.0859 0.9475 0.0273
-7.750 -0.0687 0.07278 0.07044 -0.0893 0.9320 0.0278
-7.500 -0.0430 0.06861 0.06622 -0.0968 0.9117 0.0282
-7.250 0.0018 0.06311 0.06059 -0.1098 0.8885 0.0295
-6.750 0.0532 0.05133 0.04814 -0.1302 0.8288 0.0312
-6.500 0.0646 0.04942 0.04612 -0.1295 0.8146 0.0315
-6.250 0.0750 0.04768 0.04428 -0.1286 0.8024 0.0317
-6.000 0.0858 0.04605 0.04258 -0.1276 0.7930 0.0321
-5.750 0.0969 0.04428 0.04071 -0.1266 0.7836 0.0325
-5.500 0.1071 0.04235 0.03870 -0.1254 0.7751 0.0332
-5.250 0.1186 0.04026 0.03648 -0.1242 0.7675 0.0341
-5.000 0.1243 0.03572 0.03147 -0.1214 0.7608 0.0363
-4.750 0.1363 0.03410 0.02984 -0.1197 0.7535 0.0367
-4.500 0.1515 0.03275 0.02838 -0.1183 0.7467 0.0370
-4.250 0.1658 0.03154 0.02714 -0.1165 0.7401 0.0375
-4.000 0.1811 0.03022 0.02570 -0.1147 0.7331 0.0383
-3.750 0.1969 0.02875 0.02408 -0.1127 0.7267 0.0396
-3.500 0.2073 0.02602 0.02094 -0.1086 0.7204 0.0426
-3.250 0.2251 0.02497 0.01983 -0.1071 0.7145 0.0431
-3.000 0.2437 0.02413 0.01894 -0.1057 0.7092 0.0440
-2.750 0.2619 0.02319 0.01791 -0.1038 0.7031 0.0458
-2.500 0.2774 0.02154 0.01589 -0.1007 0.6976 0.0497
-2.250 0.2974 0.02069 0.01500 -0.0993 0.6923 0.0506
-2.000 0.3171 0.01995 0.01421 -0.0977 0.6865 0.0523
-1.750 0.3359 0.01903 0.01295 -0.0952 0.6812 0.0577
-1.500 0.3571 0.01818 0.01209 -0.0941 0.6757 0.0590
-1.250 0.3780 0.01758 0.01146 -0.0926 0.6694 0.0616
-0.750 0.1566 0.02088 0.01668 -0.0460 0.6593 0.0488
-0.500 0.4450 0.01518 0.00835 -0.0870 0.6507 0.0563
-0.250 0.4679 0.01428 0.00748 -0.0863 0.6446 0.0622
0.000 0.4895 0.01395 0.00715 -0.0851 0.6373 0.0700
0.250 0.5256 0.01154 0.00425 -0.0850 0.6307 0.0409
0.500 0.5488 0.01123 0.00390 -0.0838 0.6227 0.0411
0.750 0.5712 0.01102 0.00365 -0.0825 0.6139 0.0416
1.000 0.5934 0.01085 0.00346 -0.0811 0.6052 0.0419
1.250 0.6139 0.01059 0.00318 -0.0794 0.5956 0.0428
1.500 0.6351 0.01045 0.00305 -0.0779 0.5852 0.0443
1.750 0.6557 0.01040 0.00297 -0.0762 0.5737 0.0463
2.000 0.6753 0.01037 0.00289 -0.0743 0.5602 0.0480
2.250 0.6942 0.01037 0.00283 -0.0723 0.5440 0.0492
2.500 0.7120 0.01039 0.00281 -0.0700 0.5238 0.0542
2.750 0.7277 0.01048 0.00284 -0.0673 0.4994 0.0667
3.000 0.9768 0.01030 0.00414 -0.1188 0.4089 1.0000
3.250 0.9956 0.01061 0.00432 -0.1169 0.3925 1.0000
3.500 1.0144 0.01092 0.00452 -0.1151 0.3800 1.0000
3.750 1.0348 0.01115 0.00470 -0.1137 0.3703 1.0000
4.000 1.0541 0.01143 0.00491 -0.1120 0.3625 1.0000
4.250 1.0748 0.01165 0.00510 -0.1106 0.3556 1.0000
4.500 1.0937 0.01194 0.00532 -0.1088 0.3493 1.0000
4.750 1.1141 0.01216 0.00553 -0.1074 0.3441 1.0000
5.000 1.1344 0.01238 0.00574 -0.1059 0.3392 1.0000
5.250 1.1533 0.01265 0.00598 -0.1042 0.3348 1.0000
5.500 1.1712 0.01298 0.00626 -0.1023 0.3306 1.0000
5.750 1.1918 0.01316 0.00648 -0.1009 0.3275 1.0000
6.000 1.2115 0.01337 0.00671 -0.0993 0.3242 1.0000
6.250 1.2298 0.01362 0.00696 -0.0975 0.3208 1.0000
6.500 1.2443 0.01395 0.00724 -0.0950 0.3159 1.0000
6.750 1.2611 0.01419 0.00751 -0.0928 0.3127 1.0000
7.000 1.2781 0.01434 0.00770 -0.0908 0.3083 1.0000
7.250 1.2944 0.01456 0.00794 -0.0886 0.3044 1.0000
7.500 1.3093 0.01488 0.00823 -0.0862 0.3004 1.0000
7.750 1.3254 0.01520 0.00856 -0.0841 0.2968 1.0000
8.000 1.3431 0.01539 0.00882 -0.0823 0.2937 1.0000
8.250 1.3598 0.01560 0.00908 -0.0803 0.2896 1.0000
8.500 1.3750 0.01591 0.00938 -0.0781 0.2854 1.0000
8.750 1.3896 0.01633 0.00979 -0.0759 0.2814 1.0000
9.000 1.4073 0.01651 0.01007 -0.0742 0.2779 1.0000
9.250 1.4240 0.01677 0.01038 -0.0724 0.2735 1.0000
9.500 1.4387 0.01712 0.01075 -0.0703 0.2694 1.0000
9.750 1.4527 0.01755 0.01119 -0.0681 0.2651 1.0000
10.000 1.4702 0.01779 0.01153 -0.0666 0.2605 1.0000
10.250 1.4841 0.01819 0.01195 -0.0645 0.2541 1.0000
10.500 1.4982 0.01861 0.01240 -0.0625 0.2473 1.0000
10.750 1.5116 0.01907 0.01289 -0.0604 0.2387 1.0000
11.000 1.5246 0.01959 0.01343 -0.0584 0.2282 1.0000
11.250 1.5335 0.02033 0.01413 -0.0559 0.2113 1.0000
11.500 1.5321 0.02171 0.01531 -0.0523 0.1770 1.0000
11.750 1.5124 0.02439 0.01762 -0.0469 0.1246 1.0000
12.000 1.4973 0.02708 0.02013 -0.0427 0.0928 1.0000
12.250 1.4800 0.03019 0.02302 -0.0388 0.0589 1.0000
12.500 1.4746 0.03255 0.02535 -0.0363 0.0489 1.0000
13.000 1.4735 0.03675 0.02967 -0.0327 0.0418 1.0000
13.250 1.4731 0.03895 0.03193 -0.0312 0.0397 1.0000
13.500 1.4676 0.04172 0.03476 -0.0296 0.0377 1.0000
13.750 1.4665 0.04415 0.03729 -0.0283 0.0366 1.0000
14.000 1.4662 0.04657 0.03981 -0.0273 0.0353 1.0000
14.250 1.4633 0.04935 0.04269 -0.0264 0.0342 1.0000
14.500 1.4590 0.05238 0.04580 -0.0256 0.0334 1.0000
14.750 1.4479 0.05628 0.04978 -0.0249 0.0322 1.0000
15.000 1.4367 0.06039 0.05400 -0.0245 0.0316 1.0000
15.250 1.4294 0.06417 0.05789 -0.0243 0.0310 1.0000
15.500 1.4251 0.06764 0.06147 -0.0243 0.0303 1.0000
15.750 1.4174 0.07167 0.06561 -0.0244 0.0295 1.0000
16.000 1.4094 0.07583 0.06987 -0.0247 0.0290 1.0000
16.250 1.4006 0.08018 0.07433 -0.0252 0.0285 1.0000
16.500 1.3915 0.08463 0.07887 -0.0258 0.0280 1.0000
16.750 1.3808 0.08940 0.08373 -0.0265 0.0277 1.0000
17.000 1.3693 0.09433 0.08874 -0.0274 0.0271 1.0000
17.250 1.3567 0.09940 0.09386 -0.0283 0.0266 1.0000
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