GOE 628 AIRFOIL (goe628-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 628 AIRFOIL (goe628-il) Reynolds number: 200,000 Max Cl/Cd: 63.36 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe628-il-200000-n5.txt Download as CSV file: xf-goe628-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 628 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6423 0.04406 0.03904 -0.1104 0.9780 0.0517
-12.250 -0.6481 0.03931 0.03385 -0.1173 0.9627 0.0525
-12.000 -0.6323 0.03672 0.03101 -0.1204 0.9542 0.0534
-11.750 -0.6063 0.03555 0.02987 -0.1217 0.9473 0.0544
-11.500 -0.5818 0.03408 0.02831 -0.1234 0.9395 0.0554
-11.250 -0.5586 0.03251 0.02658 -0.1249 0.9313 0.0563
-11.000 -0.5359 0.03092 0.02477 -0.1261 0.9219 0.0570
-10.750 -0.5132 0.02950 0.02313 -0.1268 0.9123 0.0577
-10.500 -0.4887 0.02817 0.02156 -0.1277 0.9025 0.0584
-10.250 -0.4662 0.02704 0.02021 -0.1277 0.8912 0.0589
-10.000 -0.4394 0.02597 0.01891 -0.1283 0.8815 0.0593
-9.750 -0.4165 0.02492 0.01781 -0.1278 0.8690 0.0598
-9.500 -0.3908 0.02399 0.01684 -0.1278 0.8578 0.0604
-9.250 -0.3660 0.02321 0.01599 -0.1276 0.8456 0.0610
-9.000 -0.3424 0.02250 0.01521 -0.1271 0.8330 0.0617
-8.750 -0.3177 0.02182 0.01442 -0.1267 0.8211 0.0623
-8.500 -0.2936 0.02118 0.01367 -0.1261 0.8088 0.0629
-8.250 -0.2697 0.02059 0.01297 -0.1255 0.7973 0.0635
-8.000 -0.2448 0.02003 0.01228 -0.1250 0.7868 0.0641
-7.750 -0.2210 0.01952 0.01168 -0.1242 0.7759 0.0646
-7.500 -0.1962 0.01905 0.01108 -0.1236 0.7667 0.0652
-7.250 -0.1720 0.01863 0.01056 -0.1229 0.7571 0.0658
-7.000 -0.1472 0.01819 0.01002 -0.1223 0.7488 0.0666
-6.750 -0.1239 0.01772 0.00955 -0.1216 0.7400 0.0675
-6.500 -0.0992 0.01734 0.00911 -0.1210 0.7322 0.0685
-6.250 -0.0745 0.01700 0.00871 -0.1203 0.7247 0.0695
-6.000 -0.0496 0.01670 0.00833 -0.1197 0.7168 0.0705
-5.500 0.0011 0.01616 0.00764 -0.1185 0.7025 0.0727
-5.250 0.0266 0.01591 0.00731 -0.1180 0.6949 0.0740
-5.000 0.0518 0.01565 0.00699 -0.1173 0.6865 0.0758
-4.750 0.0767 0.01541 0.00670 -0.1166 0.6763 0.0780
-4.500 0.1023 0.01522 0.00641 -0.1160 0.6672 0.0812
-4.250 0.1276 0.01497 0.00617 -0.1154 0.6584 0.0863
-4.000 0.1536 0.01475 0.00591 -0.1149 0.6515 0.0953
-3.750 0.1790 0.01448 0.00570 -0.1143 0.6441 0.1125
-3.500 0.2044 0.01420 0.00549 -0.1138 0.6365 0.1395
-3.250 0.2303 0.01400 0.00536 -0.1133 0.6299 0.1700
-3.000 0.2562 0.01389 0.00531 -0.1128 0.6222 0.1948
-2.750 0.2825 0.01384 0.00524 -0.1122 0.6148 0.2158
-2.500 0.3088 0.01381 0.00521 -0.1117 0.6072 0.2329
-2.250 0.3349 0.01379 0.00519 -0.1112 0.5991 0.2465
-2.000 0.3613 0.01380 0.00515 -0.1106 0.5920 0.2570
-1.750 0.3875 0.01381 0.00514 -0.1101 0.5839 0.2678
-1.500 0.4135 0.01384 0.00512 -0.1095 0.5760 0.2783
-1.250 0.4396 0.01387 0.00511 -0.1089 0.5673 0.2891
-1.000 0.4651 0.01390 0.00512 -0.1082 0.5588 0.2982
-0.750 0.4910 0.01395 0.00512 -0.1076 0.5502 0.3086
-0.500 0.5162 0.01399 0.00517 -0.1069 0.5416 0.3185
-0.250 0.5418 0.01407 0.00519 -0.1063 0.5331 0.3289
0.000 0.5666 0.01412 0.00524 -0.1055 0.5236 0.3381
0.500 0.6159 0.01426 0.00531 -0.1039 0.5041 0.3556
0.750 0.6406 0.01434 0.00535 -0.1032 0.4944 0.3639
1.000 0.6645 0.01442 0.00539 -0.1023 0.4847 0.3705
1.250 0.6887 0.01450 0.00546 -0.1014 0.4750 0.3774
1.500 0.7121 0.01463 0.00551 -0.1005 0.4653 0.3853
1.750 0.7355 0.01471 0.00562 -0.0995 0.4547 0.3928
2.000 0.7581 0.01485 0.00571 -0.0984 0.4448 0.4009
2.250 0.7809 0.01498 0.00582 -0.0974 0.4342 0.4088
2.500 0.8030 0.01512 0.00595 -0.0962 0.4251 0.4180
2.750 0.8252 0.01527 0.00608 -0.0951 0.4159 0.4278
3.000 0.8468 0.01543 0.00624 -0.0939 0.4078 0.4384
3.250 0.8683 0.01559 0.00641 -0.0927 0.3993 0.4495
3.500 0.8888 0.01579 0.00659 -0.0913 0.3918 0.4630
3.750 0.9100 0.01593 0.00679 -0.0901 0.3842 0.4796
4.000 0.9297 0.01613 0.00700 -0.0886 0.3773 0.5000
4.250 0.9501 0.01626 0.00723 -0.0873 0.3711 0.5287
4.500 0.9692 0.01632 0.00748 -0.0857 0.3654 0.5890
5.000 1.0403 0.01643 0.00817 -0.0892 0.3539 1.0000
5.250 1.0593 0.01672 0.00843 -0.0876 0.3488 1.0000
5.500 1.0772 0.01706 0.00871 -0.0859 0.3440 1.0000
5.750 1.0950 0.01745 0.00901 -0.0842 0.3401 1.0000
6.000 1.1150 0.01775 0.00933 -0.0829 0.3362 1.0000
6.250 1.1343 0.01809 0.00966 -0.0815 0.3323 1.0000
6.500 1.1530 0.01846 0.01001 -0.0800 0.3287 1.0000
6.750 1.1712 0.01886 0.01037 -0.0785 0.3252 1.0000
7.000 1.1896 0.01930 0.01075 -0.0771 0.3219 1.0000
7.250 1.2086 0.01966 0.01116 -0.0758 0.3184 1.0000
7.500 1.2271 0.02006 0.01159 -0.0745 0.3150 1.0000
7.750 1.2453 0.02050 0.01203 -0.0732 0.3118 1.0000
8.000 1.2633 0.02096 0.01247 -0.0718 0.3089 1.0000
8.250 1.2815 0.02146 0.01294 -0.0706 0.3061 1.0000
8.500 1.2996 0.02194 0.01343 -0.0693 0.3032 1.0000
8.750 1.3168 0.02242 0.01398 -0.0680 0.3002 1.0000
9.000 1.3336 0.02293 0.01454 -0.0667 0.2972 1.0000
9.250 1.3503 0.02347 0.01511 -0.0654 0.2944 1.0000
9.500 1.3668 0.02403 0.01568 -0.0641 0.2916 1.0000
9.750 1.3840 0.02462 0.01624 -0.0629 0.2889 1.0000
10.000 1.4003 0.02524 0.01689 -0.0617 0.2862 1.0000
10.250 1.4145 0.02589 0.01764 -0.0603 0.2833 1.0000
10.500 1.4279 0.02659 0.01842 -0.0589 0.2799 1.0000
10.750 1.4405 0.02732 0.01920 -0.0574 0.2765 1.0000
11.000 1.4533 0.02809 0.01996 -0.0560 0.2731 1.0000
11.250 1.4679 0.02885 0.02071 -0.0549 0.2701 1.0000
11.500 1.4783 0.02977 0.02176 -0.0534 0.2669 1.0000
11.750 1.4898 0.03069 0.02279 -0.0521 0.2639 1.0000
12.000 1.5010 0.03165 0.02382 -0.0509 0.2610 1.0000
12.250 1.5120 0.03264 0.02485 -0.0497 0.2581 1.0000
12.500 1.5238 0.03361 0.02582 -0.0486 0.2553 1.0000
12.750 1.5346 0.03470 0.02698 -0.0476 0.2526 1.0000
13.000 1.5424 0.03600 0.02842 -0.0464 0.2496 1.0000
13.250 1.5503 0.03732 0.02985 -0.0454 0.2465 1.0000
13.500 1.5582 0.03867 0.03127 -0.0444 0.2436 1.0000
13.750 1.5664 0.04000 0.03265 -0.0435 0.2406 1.0000
14.000 1.5761 0.04126 0.03390 -0.0426 0.2378 1.0000
14.250 1.5789 0.04316 0.03598 -0.0418 0.2345 1.0000
14.500 1.5825 0.04504 0.03799 -0.0410 0.2310 1.0000
14.750 1.5867 0.04690 0.03993 -0.0403 0.2277 1.0000
15.000 1.5920 0.04866 0.04173 -0.0397 0.2246 1.0000
15.250 1.5960 0.05061 0.04373 -0.0391 0.2214 1.0000
15.500 1.5937 0.05331 0.04661 -0.0388 0.2171 1.0000
15.750 1.5929 0.05590 0.04929 -0.0385 0.2129 1.0000
16.000 1.5936 0.05832 0.05172 -0.0382 0.2090 1.0000
16.250 1.5902 0.06136 0.05489 -0.0381 0.2048 1.0000
16.500 1.5847 0.06475 0.05841 -0.0383 0.2001 1.0000
16.750 1.5818 0.06783 0.06154 -0.0384 0.1958 1.0000
17.000 1.5790 0.07098 0.06476 -0.0386 0.1921 1.0000
17.250 1.5695 0.07516 0.06909 -0.0392 0.1874 1.0000
17.500 1.5626 0.07900 0.07301 -0.0398 0.1831 1.0000
17.750 1.5585 0.08247 0.07649 -0.0404 0.1791 1.0000
18.000 1.5443 0.08756 0.08176 -0.0415 0.1744 1.0000
18.250 1.5327 0.09228 0.08656 -0.0427 0.1694 1.0000
18.500 1.5253 0.09643 0.09074 -0.0437 0.1652 1.0000
18.750 1.5073 0.10234 0.09680 -0.0455 0.1603 1.0000
19.000 1.4972 0.10705 0.10153 -0.0470 0.1550 1.0000
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Polar data table (+)
Polar graphs
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