GOE 625 AIRFOIL (goe625-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 625 AIRFOIL (goe625-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.7 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe625-il-1000000-n5.txt Download as CSV file: xf-goe625-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 625 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.6857 0.10182 0.09912 -0.0824 1.0000 0.0321
-18.000 -0.7271 0.09164 0.08884 -0.0892 0.9960 0.0325
-17.750 -1.0630 0.03764 0.03379 -0.1313 0.9635 0.0315
-17.500 -1.0814 0.03194 0.02785 -0.1361 0.9409 0.0317
-17.250 -1.0870 0.02897 0.02470 -0.1373 0.9238 0.0320
-17.000 -1.0861 0.02697 0.02256 -0.1373 0.9108 0.0323
-16.750 -1.0814 0.02548 0.02095 -0.1366 0.8999 0.0327
-16.500 -1.0735 0.02429 0.01965 -0.1356 0.8914 0.0331
-16.250 -1.0637 0.02332 0.01857 -0.1343 0.8828 0.0335
-16.000 -1.0529 0.02252 0.01767 -0.1326 0.8754 0.0339
-15.750 -1.0412 0.02178 0.01686 -0.1309 0.8681 0.0344
-15.500 -1.0260 0.02100 0.01600 -0.1297 0.8618 0.0351
-15.250 -1.0083 0.02031 0.01525 -0.1288 0.8567 0.0357
-15.000 -0.9889 0.01969 0.01457 -0.1279 0.8507 0.0364
-14.750 -0.9687 0.01914 0.01394 -0.1271 0.8435 0.0372
-14.500 -0.9472 0.01864 0.01337 -0.1264 0.8369 0.0379
-14.250 -0.9253 0.01812 0.01279 -0.1257 0.8304 0.0387
-14.000 -0.9031 0.01761 0.01223 -0.1251 0.8245 0.0397
-13.750 -0.8800 0.01716 0.01172 -0.1245 0.8192 0.0408
-13.500 -0.8559 0.01674 0.01126 -0.1241 0.8131 0.0420
-13.250 -0.8317 0.01635 0.01081 -0.1236 0.8063 0.0432
-13.000 -0.8071 0.01598 0.01040 -0.1232 0.8005 0.0446
-12.750 -0.7815 0.01563 0.01003 -0.1228 0.7954 0.0459
-12.500 -0.7557 0.01533 0.00967 -0.1225 0.7892 0.0471
-12.250 -0.7300 0.01504 0.00934 -0.1222 0.7831 0.0484
-12.000 -0.7034 0.01476 0.00904 -0.1220 0.7776 0.0498
-11.750 -0.6767 0.01452 0.00875 -0.1218 0.7703 0.0511
-11.500 -0.6502 0.01431 0.00846 -0.1215 0.7622 0.0522
-11.250 -0.6232 0.01407 0.00820 -0.1213 0.7541 0.0533
-11.000 -0.5961 0.01388 0.00797 -0.1211 0.7460 0.0545
-10.750 -0.5684 0.01370 0.00775 -0.1210 0.7405 0.0557
-10.500 -0.5406 0.01351 0.00752 -0.1209 0.7346 0.0568
-10.250 -0.5130 0.01334 0.00729 -0.1208 0.7282 0.0576
-10.000 -0.4855 0.01314 0.00705 -0.1207 0.7225 0.0584
-9.750 -0.4576 0.01295 0.00684 -0.1206 0.7160 0.0593
-9.500 -0.4299 0.01280 0.00664 -0.1205 0.7083 0.0601
-9.250 -0.4018 0.01265 0.00645 -0.1204 0.7008 0.0609
-9.000 -0.3739 0.01252 0.00627 -0.1203 0.6915 0.0618
-8.750 -0.3459 0.01240 0.00609 -0.1203 0.6827 0.0626
-8.500 -0.3177 0.01229 0.00592 -0.1202 0.6729 0.0633
-8.250 -0.2896 0.01219 0.00576 -0.1201 0.6636 0.0638
-8.000 -0.2624 0.01201 0.00552 -0.1200 0.6522 0.0646
-7.750 -0.2347 0.01187 0.00534 -0.1199 0.6407 0.0653
-7.500 -0.2073 0.01178 0.00518 -0.1197 0.6272 0.0660
-7.250 -0.1799 0.01171 0.00505 -0.1195 0.6115 0.0668
-7.000 -0.1525 0.01167 0.00492 -0.1193 0.5941 0.0676
-6.750 -0.1253 0.01166 0.00482 -0.1191 0.5751 0.0685
-6.500 -0.0982 0.01168 0.00474 -0.1189 0.5553 0.0694
-6.250 -0.0712 0.01171 0.00466 -0.1187 0.5352 0.0701
-6.000 -0.0442 0.01174 0.00458 -0.1184 0.5157 0.0705
-5.750 -0.0180 0.01167 0.00442 -0.1181 0.4982 0.0713
-5.500 0.0090 0.01161 0.00429 -0.1179 0.4837 0.0720
-5.250 0.0363 0.01155 0.00419 -0.1177 0.4732 0.0727
-5.000 0.0637 0.01152 0.00410 -0.1176 0.4638 0.0735
-4.750 0.0915 0.01147 0.00401 -0.1175 0.4568 0.0742
-4.500 0.1195 0.01142 0.00393 -0.1175 0.4505 0.0748
-4.250 0.1472 0.01140 0.00386 -0.1174 0.4443 0.0754
-4.000 0.1752 0.01136 0.00379 -0.1173 0.4396 0.0761
-3.750 0.2034 0.01132 0.00373 -0.1173 0.4357 0.0768
-3.500 0.2315 0.01129 0.00367 -0.1173 0.4318 0.0774
-3.250 0.2594 0.01128 0.00363 -0.1173 0.4279 0.0779
-2.750 0.3148 0.01119 0.00351 -0.1171 0.4211 0.0801
-2.500 0.3430 0.01115 0.00347 -0.1172 0.4189 0.0812
-2.250 0.3711 0.01112 0.00344 -0.1172 0.4163 0.0824
-2.000 0.3989 0.01110 0.00341 -0.1171 0.4134 0.0837
-1.750 0.4266 0.01110 0.00340 -0.1171 0.4106 0.0850
-1.500 0.4541 0.01111 0.00340 -0.1170 0.4080 0.0866
-1.250 0.4813 0.01111 0.00340 -0.1169 0.4053 0.0900
-1.000 0.5085 0.01112 0.00341 -0.1167 0.4029 0.0941
-0.750 0.5363 0.01107 0.00342 -0.1167 0.4017 0.1037
-0.500 0.5639 0.01102 0.00345 -0.1167 0.4004 0.1211
-0.250 0.5915 0.01101 0.00348 -0.1167 0.3989 0.1318
0.000 0.6190 0.01104 0.00352 -0.1166 0.3972 0.1385
0.250 0.6461 0.01106 0.00357 -0.1165 0.3949 0.1451
0.500 0.6729 0.01111 0.00362 -0.1164 0.3922 0.1504
0.750 0.6993 0.01118 0.00368 -0.1161 0.3893 0.1543
1.000 0.7251 0.01125 0.00375 -0.1158 0.3864 0.1604
1.250 0.7512 0.01132 0.00383 -0.1155 0.3841 0.1651
1.500 0.7782 0.01135 0.00388 -0.1154 0.3826 0.1693
1.750 0.8048 0.01138 0.00395 -0.1152 0.3809 0.1756
2.000 0.8310 0.01143 0.00402 -0.1150 0.3786 0.1813
2.250 0.8567 0.01150 0.00410 -0.1146 0.3762 0.1878
2.500 0.8815 0.01156 0.00419 -0.1141 0.3737 0.1989
2.750 0.9044 0.01164 0.00428 -0.1132 0.3711 0.2090
3.000 0.9257 0.01172 0.00439 -0.1121 0.3684 0.2231
3.250 0.9479 0.01176 0.00452 -0.1111 0.3662 0.2553
3.500 0.9729 0.01168 0.00466 -0.1109 0.3649 0.3379
3.750 0.9984 0.01162 0.00483 -0.1107 0.3633 0.4206
4.000 1.0241 0.01153 0.00502 -0.1106 0.3616 0.5287
4.250 1.0495 0.01133 0.00526 -0.1106 0.3597 0.6894
4.500 1.0714 0.01113 0.00553 -0.1095 0.3577 0.8511
4.750 1.0919 0.01114 0.00577 -0.1079 0.3557 0.9782
5.000 1.1185 0.01132 0.00593 -0.1080 0.3533 1.0000
5.250 1.1410 0.01155 0.00614 -0.1073 0.3508 1.0000
5.500 1.1644 0.01176 0.00634 -0.1067 0.3487 1.0000
5.750 1.1887 0.01195 0.00652 -0.1063 0.3465 1.0000
6.000 1.2124 0.01216 0.00673 -0.1059 0.3431 1.0000
6.250 1.2353 0.01241 0.00696 -0.1053 0.3394 1.0000
6.500 1.2564 0.01274 0.00725 -0.1045 0.3346 1.0000
6.750 1.2789 0.01302 0.00752 -0.1040 0.3311 1.0000
7.000 1.3020 0.01328 0.00778 -0.1035 0.3272 1.0000
7.250 1.3240 0.01360 0.00808 -0.1029 0.3228 1.0000
7.500 1.3442 0.01400 0.00845 -0.1021 0.3180 1.0000
7.750 1.3661 0.01433 0.00879 -0.1015 0.3140 1.0000
8.000 1.3869 0.01472 0.00916 -0.1008 0.3080 1.0000
8.250 1.4050 0.01525 0.00965 -0.0998 0.3007 1.0000
8.500 1.4239 0.01576 0.01012 -0.0989 0.2921 1.0000
8.750 1.4397 0.01644 0.01074 -0.0977 0.2824 1.0000
9.000 1.4542 0.01720 0.01144 -0.0963 0.2714 1.0000
9.250 1.4700 0.01790 0.01211 -0.0951 0.2629 1.0000
9.500 1.4843 0.01870 0.01287 -0.0938 0.2550 1.0000
9.750 1.5007 0.01941 0.01357 -0.0928 0.2491 1.0000
10.000 1.5151 0.02024 0.01437 -0.0916 0.2429 1.0000
10.250 1.5303 0.02103 0.01515 -0.0906 0.2381 1.0000
10.500 1.5460 0.02180 0.01593 -0.0896 0.2338 1.0000
10.750 1.5604 0.02266 0.01679 -0.0886 0.2295 1.0000
11.000 1.5731 0.02365 0.01777 -0.0874 0.2253 1.0000
11.250 1.5889 0.02446 0.01860 -0.0866 0.2222 1.0000
11.500 1.6020 0.02546 0.01961 -0.0855 0.2181 1.0000
11.750 1.6127 0.02663 0.02077 -0.0843 0.2132 1.0000
12.000 1.6235 0.02784 0.02199 -0.0832 0.2087 1.0000
12.250 1.6366 0.02891 0.02307 -0.0823 0.2050 1.0000
12.500 1.6472 0.03018 0.02436 -0.0813 0.2014 1.0000
12.750 1.6568 0.03155 0.02573 -0.0802 0.1979 1.0000
13.000 1.6664 0.03295 0.02716 -0.0793 0.1948 1.0000
13.250 1.6789 0.03415 0.02839 -0.0786 0.1922 1.0000
13.500 1.6889 0.03557 0.02984 -0.0777 0.1894 1.0000
13.750 1.6977 0.03711 0.03140 -0.0769 0.1864 1.0000
14.000 1.7030 0.03900 0.03331 -0.0759 0.1831 1.0000
14.250 1.7108 0.04066 0.03501 -0.0751 0.1802 1.0000
14.500 1.7175 0.04248 0.03686 -0.0743 0.1765 1.0000
14.750 1.7204 0.04468 0.03908 -0.0734 0.1719 1.0000
15.000 1.7213 0.04710 0.04152 -0.0724 0.1679 1.0000
15.250 1.7250 0.04932 0.04378 -0.0717 0.1643 1.0000
15.500 1.7236 0.05204 0.04653 -0.0709 0.1591 1.0000
15.750 1.7184 0.05522 0.04973 -0.0700 0.1538 1.0000
16.000 1.7108 0.05872 0.05325 -0.0692 0.1465 1.0000
16.250 1.6991 0.06275 0.05730 -0.0684 0.1397 1.0000
16.500 1.6791 0.06775 0.06232 -0.0675 0.1303 1.0000
16.750 1.6423 0.07482 0.06937 -0.0666 0.1137 1.0000
17.000 1.6071 0.08191 0.07646 -0.0661 0.1004 1.0000
17.250 1.5808 0.08807 0.08265 -0.0659 0.0918 1.0000
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