GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 673 AIRFOIL (goe673-il) Reynolds number: 50,000 Max Cl/Cd: 38.13 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe673-il-50000.txt Download as CSV file: xf-goe673-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 673 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.4209 0.08613 0.07998 -0.0158 1.0000 0.3323
-6.750 -0.4421 0.08473 0.07876 -0.0127 1.0000 0.3434
-6.500 -0.4392 0.08146 0.07555 -0.0110 1.0000 0.3478
-6.250 -0.5031 0.06124 0.05484 -0.0436 1.0000 0.1412
-6.000 -0.4962 0.05486 0.04808 -0.0454 1.0000 0.1249
-5.750 -0.4846 0.04886 0.04141 -0.0470 1.0000 0.1134
-5.500 -0.4683 0.04404 0.03601 -0.0474 1.0000 0.1070
-5.250 -0.4469 0.03999 0.03104 -0.0475 1.0000 0.1021
-5.000 -0.4246 0.03683 0.02744 -0.0471 1.0000 0.1012
-4.750 -0.4004 0.03424 0.02424 -0.0467 1.0000 0.1035
-4.500 -0.3772 0.03206 0.02201 -0.0463 1.0000 0.1089
-4.250 -0.3511 0.03007 0.01960 -0.0456 1.0000 0.1127
-4.000 -0.3244 0.02828 0.01757 -0.0449 1.0000 0.1187
-3.750 -0.2990 0.02691 0.01618 -0.0442 1.0000 0.1335
-3.500 -0.2731 0.02552 0.01485 -0.0436 1.0000 0.1608
-3.250 -0.2435 0.02197 0.01347 -0.0436 1.0000 0.4732
-3.000 -0.2335 0.02170 0.01389 -0.0384 1.0000 0.6400
-2.750 -0.2333 0.02172 0.01432 -0.0301 1.0000 0.7596
-2.500 -0.2331 0.02140 0.01424 -0.0218 1.0000 0.8611
-2.250 -0.1768 0.02093 0.01331 -0.0284 1.0000 1.0000
-2.000 -0.1551 0.02080 0.01265 -0.0306 1.0000 1.0000
-1.750 -0.1313 0.02100 0.01239 -0.0319 1.0000 1.0000
-1.500 -0.1083 0.02130 0.01227 -0.0326 1.0000 1.0000
-1.250 -0.0859 0.02167 0.01232 -0.0331 1.0000 1.0000
-1.000 -0.0640 0.02211 0.01247 -0.0335 1.0000 1.0000
-0.750 -0.0425 0.02260 0.01271 -0.0339 1.0000 1.0000
-0.500 -0.0213 0.02315 0.01301 -0.0342 1.0000 1.0000
-0.250 -0.0005 0.02375 0.01341 -0.0345 1.0000 1.0000
0.000 0.0200 0.02440 0.01389 -0.0348 1.0000 1.0000
0.250 0.0401 0.02510 0.01445 -0.0351 1.0000 1.0000
0.500 0.0599 0.02586 0.01506 -0.0354 1.0000 1.0000
0.750 0.0794 0.02667 0.01576 -0.0357 1.0000 1.0000
1.000 0.1222 0.02783 0.01679 -0.0404 0.9898 1.0000
1.250 0.1699 0.02903 0.01790 -0.0459 0.9759 1.0000
1.500 0.2147 0.03016 0.01895 -0.0507 0.9617 1.0000
1.750 0.2571 0.03121 0.01996 -0.0550 0.9472 1.0000
2.000 0.2978 0.03220 0.02094 -0.0587 0.9326 1.0000
2.250 0.3374 0.03315 0.02191 -0.0621 0.9178 1.0000
2.500 0.3757 0.03405 0.02284 -0.0651 0.9030 1.0000
2.750 0.4134 0.03490 0.02375 -0.0679 0.8881 1.0000
3.000 0.4510 0.03570 0.02466 -0.0705 0.8732 1.0000
3.250 0.4885 0.03645 0.02551 -0.0729 0.8583 1.0000
3.500 0.5168 0.03725 0.02641 -0.0738 0.8422 1.0000
3.750 0.5451 0.03804 0.02736 -0.0746 0.8258 1.0000
4.000 0.5757 0.03878 0.02824 -0.0756 0.8098 1.0000
4.250 0.6077 0.03944 0.02907 -0.0767 0.7939 1.0000
4.500 0.6411 0.04001 0.02983 -0.0777 0.7783 1.0000
4.750 0.6760 0.04046 0.03054 -0.0787 0.7628 1.0000
5.000 0.7117 0.04079 0.03113 -0.0797 0.7476 1.0000
5.250 0.7483 0.04100 0.03162 -0.0804 0.7327 1.0000
5.500 0.7648 0.04217 0.03300 -0.0792 0.7151 1.0000
5.750 0.7890 0.04298 0.03413 -0.0787 0.6987 1.0000
6.000 0.8166 0.04365 0.03511 -0.0784 0.6832 1.0000
6.250 0.8451 0.04423 0.03605 -0.0780 0.6680 1.0000
6.500 0.9543 0.02503 0.01701 -0.0603 0.4898 1.0000
6.750 0.9409 0.02624 0.01700 -0.0517 0.2897 1.0000
7.000 0.9288 0.02967 0.01897 -0.0466 0.1538 1.0000
7.250 0.9299 0.03226 0.02114 -0.0432 0.1250 1.0000
7.500 0.9349 0.03436 0.02318 -0.0400 0.1131 1.0000
7.750 0.9468 0.03641 0.02522 -0.0374 0.1052 1.0000
8.000 0.9839 0.03879 0.02747 -0.0375 0.0947 1.0000
8.250 1.0365 0.04141 0.03028 -0.0393 0.0869 1.0000
8.500 1.0896 0.04523 0.03424 -0.0415 0.0848 1.0000
8.750 1.1226 0.04893 0.03830 -0.0414 0.0846 1.0000
9.000 1.1477 0.05322 0.04290 -0.0409 0.0835 1.0000
9.250 1.1655 0.05782 0.04787 -0.0397 0.0830 1.0000
9.500 1.1729 0.06046 0.05111 -0.0367 0.0840 1.0000
9.750 1.1631 0.06343 0.05495 -0.0322 0.0870 1.0000
10.000 1.1577 0.06771 0.05975 -0.0291 0.0901 1.0000
10.250 1.1535 0.07232 0.06470 -0.0266 0.0929 1.0000
10.500 1.1598 0.07750 0.07011 -0.0254 0.0966 1.0000
10.750 1.1236 0.08032 0.07338 -0.0209 0.0981 1.0000
11.000 1.0900 0.08422 0.07754 -0.0184 0.0993 1.0000
11.250 1.0560 0.08909 0.08263 -0.0179 0.1001 1.0000
11.500 1.0215 0.09511 0.08879 -0.0196 0.1009 1.0000
11.750 0.9845 0.10296 0.09675 -0.0238 0.1025 1.0000
12.000 0.9614 0.11132 0.10513 -0.0283 0.1059 1.0000
12.250 0.9130 0.12776 0.12153 -0.0411 0.1179 1.0000
12.500 0.8955 0.13932 0.13299 -0.0482 0.1321 1.0000
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Polar data table (+)
Polar graphs
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