GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 413 AIRFOIL (goe413-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.84 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe413-il-1000000.txt Download as CSV file: xf-goe413-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 413 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.8430 0.05927 0.05649 -0.0745 1.0000 0.0366
-14.250 -0.8642 0.05163 0.04864 -0.0825 0.9496 0.0367
-14.000 -0.8802 0.04619 0.04293 -0.0873 0.9096 0.0368
-13.750 -0.8872 0.04156 0.03807 -0.0923 0.8914 0.0369
-13.500 -0.8882 0.03764 0.03397 -0.0971 0.8786 0.0371
-13.250 -0.8854 0.03459 0.03074 -0.1012 0.8688 0.0372
-13.000 -0.8761 0.03254 0.02853 -0.1032 0.8612 0.0374
-12.750 -0.8619 0.03093 0.02676 -0.1043 0.8547 0.0377
-12.500 -0.8449 0.02943 0.02515 -0.1051 0.8500 0.0379
-12.250 -0.8263 0.02809 0.02367 -0.1057 0.8447 0.0382
-12.000 -0.8063 0.02689 0.02233 -0.1061 0.8393 0.0385
-11.750 -0.7850 0.02583 0.02113 -0.1065 0.8339 0.0387
-11.500 -0.7621 0.02486 0.02005 -0.1068 0.8299 0.0389
-11.250 -0.7382 0.02405 0.01913 -0.1071 0.8254 0.0392
-11.000 -0.7134 0.02344 0.01840 -0.1073 0.8206 0.0393
-10.750 -0.6917 0.02189 0.01670 -0.1075 0.8153 0.0398
-10.500 -0.6670 0.02085 0.01565 -0.1077 0.8110 0.0401
-10.250 -0.6411 0.02014 0.01492 -0.1079 0.8061 0.0404
-10.000 -0.6149 0.01954 0.01426 -0.1080 0.8009 0.0406
-9.750 -0.5884 0.01901 0.01366 -0.1081 0.7954 0.0409
-9.500 -0.5613 0.01846 0.01308 -0.1083 0.7908 0.0412
-9.250 -0.5340 0.01793 0.01251 -0.1084 0.7851 0.0415
-9.000 -0.5068 0.01742 0.01194 -0.1085 0.7786 0.0418
-8.750 -0.4794 0.01693 0.01139 -0.1086 0.7722 0.0422
-8.500 -0.4516 0.01643 0.01084 -0.1088 0.7650 0.0425
-8.250 -0.4239 0.01597 0.01031 -0.1089 0.7571 0.0429
-8.000 -0.3958 0.01553 0.00982 -0.1090 0.7491 0.0432
-7.750 -0.3676 0.01514 0.00936 -0.1091 0.7389 0.0435
-7.500 -0.3390 0.01486 0.00900 -0.1092 0.7278 0.0438
-7.250 -0.3104 0.01468 0.00872 -0.1093 0.7139 0.0441
-7.000 -0.2836 0.01381 0.00780 -0.1094 0.6982 0.0446
-6.750 -0.2559 0.01330 0.00724 -0.1095 0.6830 0.0450
-6.500 -0.2276 0.01295 0.00684 -0.1096 0.6697 0.0454
-6.000 -0.1704 0.01241 0.00620 -0.1099 0.6477 0.0463
-5.750 -0.1417 0.01219 0.00590 -0.1100 0.6380 0.0467
-5.500 -0.1125 0.01194 0.00562 -0.1102 0.6309 0.0472
-5.250 -0.0834 0.01172 0.00536 -0.1103 0.6239 0.0477
-5.000 -0.0544 0.01154 0.00512 -0.1105 0.6171 0.0482
-4.750 -0.0248 0.01133 0.00490 -0.1107 0.6120 0.0486
-4.500 0.0047 0.01120 0.00473 -0.1109 0.6063 0.0490
-4.250 0.0337 0.01090 0.00437 -0.1111 0.6006 0.0497
-4.000 0.0631 0.01059 0.00404 -0.1114 0.5957 0.0504
-3.750 0.0928 0.01036 0.00381 -0.1116 0.5913 0.0511
-3.500 0.1225 0.01020 0.00363 -0.1119 0.5861 0.0517
-3.250 0.1519 0.01009 0.00347 -0.1120 0.5804 0.0525
-3.000 0.1817 0.00996 0.00332 -0.1122 0.5757 0.0532
-2.750 0.2116 0.00982 0.00318 -0.1125 0.5714 0.0539
-2.500 0.2414 0.00973 0.00306 -0.1127 0.5668 0.0545
-2.250 0.2710 0.00958 0.00287 -0.1129 0.5621 0.0556
-2.000 0.3007 0.00946 0.00273 -0.1131 0.5574 0.0571
-1.750 0.3308 0.00933 0.00262 -0.1134 0.5541 0.0584
-1.500 0.3607 0.00925 0.00253 -0.1136 0.5501 0.0597
-1.250 0.3905 0.00918 0.00244 -0.1138 0.5459 0.0612
-1.000 0.4201 0.00911 0.00235 -0.1139 0.5411 0.0640
-0.750 0.4499 0.00904 0.00229 -0.1142 0.5371 0.0687
-0.500 0.4801 0.00863 0.00217 -0.1147 0.5338 0.1465
-0.250 0.5100 0.00851 0.00216 -0.1150 0.5297 0.1751
0.000 0.5396 0.00845 0.00216 -0.1153 0.5251 0.1984
0.250 0.5689 0.00845 0.00218 -0.1154 0.5200 0.2180
0.500 0.5989 0.00838 0.00219 -0.1157 0.5168 0.2395
0.750 0.6288 0.00830 0.00221 -0.1160 0.5128 0.2647
1.000 0.6585 0.00826 0.00224 -0.1162 0.5081 0.2933
1.250 0.6877 0.00826 0.00229 -0.1164 0.5028 0.3223
1.500 0.7174 0.00822 0.00234 -0.1166 0.4977 0.3515
1.750 0.7470 0.00820 0.00237 -0.1169 0.4915 0.3772
2.000 0.7762 0.00822 0.00242 -0.1170 0.4853 0.4001
2.250 0.8055 0.00824 0.00249 -0.1172 0.4797 0.4247
2.500 0.8351 0.00819 0.00255 -0.1174 0.4735 0.4613
2.750 0.8640 0.00821 0.00264 -0.1176 0.4658 0.5080
3.000 0.8932 0.00822 0.00274 -0.1178 0.4595 0.5479
3.250 0.9223 0.00824 0.00283 -0.1179 0.4525 0.5815
3.500 0.9508 0.00832 0.00293 -0.1180 0.4447 0.6130
3.750 0.9798 0.00832 0.00302 -0.1181 0.4370 0.6427
4.000 1.0078 0.00838 0.00316 -0.1181 0.4270 0.6930
4.250 1.0355 0.00833 0.00332 -0.1180 0.4162 0.7848
4.500 1.0599 0.00832 0.00348 -0.1171 0.4054 0.8689
4.750 1.0815 0.00829 0.00356 -0.1155 0.3946 1.0000
5.000 1.1095 0.00848 0.00370 -0.1155 0.3837 1.0000
5.250 1.1369 0.00873 0.00387 -0.1154 0.3715 1.0000
5.500 1.1641 0.00899 0.00405 -0.1154 0.3592 1.0000
5.750 1.1913 0.00923 0.00424 -0.1153 0.3476 1.0000
6.000 1.2178 0.00952 0.00445 -0.1151 0.3357 1.0000
6.250 1.2440 0.00983 0.00468 -0.1149 0.3236 1.0000
6.500 1.2705 0.01009 0.00490 -0.1147 0.3125 1.0000
6.750 1.2962 0.01042 0.00515 -0.1144 0.3009 1.0000
7.000 1.3211 0.01079 0.00544 -0.1140 0.2878 1.0000
7.250 1.3456 0.01118 0.00575 -0.1136 0.2724 1.0000
7.500 1.3689 0.01164 0.00610 -0.1130 0.2550 1.0000
7.750 1.3911 0.01216 0.00650 -0.1122 0.2346 1.0000
8.000 1.4092 0.01294 0.00708 -0.1109 0.2051 1.0000
8.250 1.4198 0.01417 0.00801 -0.1087 0.1603 1.0000
8.500 1.4078 0.01645 0.00980 -0.1033 0.0871 1.0000
8.750 1.4174 0.01743 0.01071 -0.1010 0.0752 1.0000
9.000 1.4311 0.01823 0.01150 -0.0993 0.0707 1.0000
9.250 1.4471 0.01895 0.01222 -0.0981 0.0687 1.0000
9.500 1.4619 0.01977 0.01306 -0.0968 0.0669 1.0000
9.750 1.4757 0.02071 0.01400 -0.0955 0.0653 1.0000
10.000 1.4886 0.02175 0.01506 -0.0943 0.0638 1.0000
10.250 1.5038 0.02264 0.01599 -0.0933 0.0633 1.0000
10.500 1.5184 0.02362 0.01699 -0.0923 0.0627 1.0000
10.750 1.5321 0.02467 0.01809 -0.0913 0.0621 1.0000
11.000 1.5446 0.02584 0.01929 -0.0903 0.0615 1.0000
11.250 1.5562 0.02711 0.02060 -0.0892 0.0609 1.0000
11.500 1.5667 0.02847 0.02200 -0.0882 0.0603 1.0000
11.750 1.5759 0.02998 0.02355 -0.0871 0.0598 1.0000
12.000 1.5838 0.03164 0.02525 -0.0861 0.0593 1.0000
12.250 1.5901 0.03347 0.02712 -0.0851 0.0587 1.0000
12.500 1.5944 0.03552 0.02923 -0.0840 0.0582 1.0000
12.750 1.5964 0.03786 0.03164 -0.0831 0.0576 1.0000
13.000 1.5966 0.04045 0.03430 -0.0821 0.0571 1.0000
13.250 1.6023 0.04252 0.03643 -0.0815 0.0570 1.0000
13.500 1.6074 0.04474 0.03871 -0.0809 0.0568 1.0000
13.750 1.6116 0.04711 0.04115 -0.0804 0.0566 1.0000
14.000 1.6147 0.04962 0.04372 -0.0799 0.0564 1.0000
14.250 1.6175 0.05219 0.04636 -0.0795 0.0562 1.0000
14.500 1.6194 0.05489 0.04913 -0.0791 0.0560 1.0000
14.750 1.6201 0.05778 0.05208 -0.0788 0.0558 1.0000
15.000 1.6206 0.06067 0.05504 -0.0785 0.0556 1.0000
15.250 1.6207 0.06365 0.05809 -0.0783 0.0554 1.0000
15.500 1.6202 0.06675 0.06126 -0.0781 0.0551 1.0000
15.750 1.6208 0.06971 0.06428 -0.0780 0.0547 1.0000
16.000 1.6198 0.07292 0.06755 -0.0779 0.0544 1.0000
16.250 1.6193 0.07607 0.07076 -0.0779 0.0540 1.0000
16.500 1.6178 0.07939 0.07414 -0.0780 0.0537 1.0000
16.750 1.6159 0.08279 0.07760 -0.0781 0.0534 1.0000
17.000 1.6142 0.08615 0.08101 -0.0782 0.0531 1.0000
17.250 1.6112 0.08973 0.08466 -0.0785 0.0528 1.0000
17.500 1.6089 0.09321 0.08819 -0.0788 0.0525 1.0000
17.750 1.6045 0.09703 0.09207 -0.0792 0.0522 1.0000
18.000 1.6017 0.10058 0.09566 -0.0796 0.0519 1.0000
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Polar data table (+)
Polar graphs
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