GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 670 AIRFOIL (goe670-il) Reynolds number: 50,000 Max Cl/Cd: 37.23 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe670-il-50000-n5.txt Download as CSV file: xf-goe670-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 670 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4038 0.10632 0.09918 -0.0335 1.0000 0.1322
-8.500 -0.4191 0.10459 0.09757 -0.0334 1.0000 0.1326
-8.250 -0.4350 0.10270 0.09581 -0.0328 1.0000 0.1328
-8.000 -0.4449 0.10009 0.09328 -0.0328 1.0000 0.1329
-7.500 -0.4475 0.08763 0.08078 -0.0346 1.0000 0.0868
-7.250 -0.4460 0.08470 0.07788 -0.0328 1.0000 0.0854
-7.000 -0.4501 0.08157 0.07477 -0.0323 1.0000 0.0849
-6.750 -0.4538 0.07829 0.07148 -0.0324 1.0000 0.0849
-6.500 -0.4559 0.07483 0.06799 -0.0327 1.0000 0.0852
-6.250 -0.4557 0.07126 0.06434 -0.0330 1.0000 0.0854
-6.000 -0.4527 0.06774 0.06073 -0.0329 1.0000 0.0850
-5.750 -0.4476 0.06423 0.05712 -0.0328 1.0000 0.0841
-5.500 -0.4407 0.06058 0.05331 -0.0329 1.0000 0.0833
-5.250 -0.4318 0.05696 0.04949 -0.0330 1.0000 0.0827
-5.000 -0.4207 0.05339 0.04567 -0.0332 1.0000 0.0823
-4.750 -0.4077 0.04999 0.04198 -0.0331 1.0000 0.0823
-4.500 -0.3929 0.04691 0.03855 -0.0330 1.0000 0.0835
-4.250 -0.3762 0.04379 0.03489 -0.0330 1.0000 0.0861
-4.000 -0.3578 0.04100 0.03153 -0.0327 0.9999 0.0874
-3.750 -0.3262 0.03843 0.02857 -0.0347 0.9949 0.0884
-3.500 -0.2951 0.03650 0.02636 -0.0364 0.9895 0.0899
-3.250 -0.2624 0.03484 0.02438 -0.0381 0.9842 0.0918
-3.000 -0.2304 0.03335 0.02255 -0.0395 0.9784 0.0947
-2.750 -0.1969 0.03212 0.02083 -0.0409 0.9725 0.1007
-2.500 -0.1640 0.03103 0.01954 -0.0423 0.9667 0.1057
-2.250 -0.1322 0.03008 0.01838 -0.0434 0.9604 0.1104
-2.000 -0.0965 0.02918 0.01712 -0.0449 0.9549 0.1167
-1.750 -0.0655 0.02858 0.01652 -0.0459 0.9479 0.1265
-1.500 -0.0288 0.02800 0.01579 -0.0477 0.9425 0.1373
-1.250 0.0029 0.02753 0.01520 -0.0485 0.9353 0.1499
-1.000 0.0395 0.02713 0.01481 -0.0505 0.9297 0.1679
-0.750 0.0684 0.02680 0.01450 -0.0509 0.9216 0.1850
-0.500 0.1042 0.02650 0.01427 -0.0527 0.9158 0.2113
-0.250 0.1305 0.02623 0.01415 -0.0527 0.9069 0.2416
0.000 0.1657 0.02571 0.01400 -0.0545 0.9011 0.3054
0.500 0.2560 0.02412 0.01398 -0.0612 0.8888 1.0000
0.750 0.2855 0.02436 0.01403 -0.0616 0.8794 1.0000
1.000 0.3212 0.02454 0.01403 -0.0631 0.8711 1.0000
1.250 0.3474 0.02475 0.01412 -0.0628 0.8596 1.0000
1.500 0.3788 0.02489 0.01417 -0.0634 0.8497 1.0000
1.750 0.4168 0.02485 0.01406 -0.0649 0.8399 1.0000
2.000 0.4498 0.02467 0.01383 -0.0652 0.8254 1.0000
2.250 0.4874 0.02422 0.01335 -0.0659 0.8095 1.0000
2.500 0.5238 0.02373 0.01284 -0.0663 0.7931 1.0000
2.750 0.5544 0.02344 0.01253 -0.0659 0.7774 1.0000
3.000 0.5819 0.02333 0.01245 -0.0652 0.7628 1.0000
3.250 0.6092 0.02321 0.01236 -0.0644 0.7477 1.0000
3.500 0.6352 0.02313 0.01233 -0.0635 0.7316 1.0000
3.750 0.6599 0.02306 0.01231 -0.0622 0.7136 1.0000
4.000 0.6874 0.02292 0.01222 -0.0614 0.6948 1.0000
4.250 0.7186 0.02269 0.01204 -0.0610 0.6753 1.0000
4.500 0.7489 0.02252 0.01190 -0.0604 0.6530 1.0000
4.750 0.7794 0.02242 0.01179 -0.0599 0.6275 1.0000
5.000 0.8051 0.02252 0.01191 -0.0588 0.5984 1.0000
5.250 0.8278 0.02273 0.01212 -0.0572 0.5655 1.0000
5.500 0.8471 0.02305 0.01243 -0.0552 0.5288 1.0000
5.750 0.8669 0.02341 0.01271 -0.0533 0.4908 1.0000
6.000 0.8882 0.02386 0.01301 -0.0516 0.4570 1.0000
6.250 0.9089 0.02447 0.01346 -0.0501 0.4280 1.0000
6.500 0.9301 0.02518 0.01408 -0.0489 0.4046 1.0000
6.750 0.9523 0.02595 0.01481 -0.0479 0.3850 1.0000
7.000 0.9755 0.02675 0.01564 -0.0471 0.3681 1.0000
7.250 0.9986 0.02757 0.01648 -0.0463 0.3522 1.0000
7.500 1.0205 0.02839 0.01735 -0.0454 0.3364 1.0000
7.750 1.0405 0.02921 0.01822 -0.0441 0.3205 1.0000
8.000 1.0601 0.03004 0.01919 -0.0429 0.3058 1.0000
8.250 1.0807 0.03093 0.02024 -0.0418 0.2931 1.0000
8.500 1.0986 0.03181 0.02126 -0.0403 0.2791 1.0000
8.750 1.1080 0.03261 0.02211 -0.0376 0.2606 1.0000
9.000 1.1126 0.03340 0.02288 -0.0343 0.2409 1.0000
9.250 1.1133 0.03425 0.02382 -0.0305 0.2213 1.0000
9.500 1.1126 0.03519 0.02488 -0.0267 0.2015 1.0000
9.750 1.1121 0.03626 0.02608 -0.0233 0.1807 1.0000
10.000 1.1133 0.03751 0.02750 -0.0203 0.1551 1.0000
10.250 1.1119 0.03912 0.02906 -0.0176 0.1253 1.0000
10.500 1.1081 0.04133 0.03102 -0.0151 0.1008 1.0000
10.750 1.1042 0.04398 0.03347 -0.0129 0.0859 1.0000
11.000 1.1021 0.04669 0.03619 -0.0110 0.0765 1.0000
11.250 1.1012 0.04942 0.03900 -0.0094 0.0692 1.0000
11.500 1.0997 0.05219 0.04185 -0.0081 0.0638 1.0000
11.750 1.0984 0.05507 0.04484 -0.0070 0.0597 1.0000
12.000 1.0987 0.05794 0.04791 -0.0061 0.0562 1.0000
12.250 1.0981 0.06096 0.05106 -0.0053 0.0539 1.0000
12.500 1.0967 0.06410 0.05428 -0.0049 0.0520 1.0000
12.750 1.0966 0.06730 0.05764 -0.0045 0.0504 1.0000
13.000 1.0949 0.07092 0.06155 -0.0044 0.0482 1.0000
13.250 1.0917 0.07475 0.06560 -0.0047 0.0466 1.0000
13.500 1.0872 0.07881 0.06986 -0.0053 0.0453 1.0000
13.750 1.0818 0.08309 0.07431 -0.0062 0.0442 1.0000
14.000 1.0764 0.08751 0.07887 -0.0073 0.0432 1.0000
14.250 1.0704 0.09220 0.08372 -0.0087 0.0426 1.0000
14.500 1.0636 0.09723 0.08889 -0.0103 0.0420 1.0000
14.750 1.0543 0.10292 0.09477 -0.0126 0.0417 1.0000
15.000 1.0402 0.10988 0.10194 -0.0161 0.0417 1.0000
15.250 1.0189 0.11894 0.11126 -0.0214 0.0419 1.0000
15.500 0.9636 0.13900 0.13166 -0.0342 0.0441 1.0000
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Polar data table (+)
Polar graphs
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