GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Reynolds number: 100,000 Max Cl/Cd: 55.9 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe278-il-100000.txt Download as CSV file: xf-goe278-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 278 (DAIMLER IX) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3630 0.09868 0.09378 -0.0259 1.0000 0.0555
-7.750 -0.3680 0.09754 0.09273 -0.0291 1.0000 0.0561
-7.500 -0.3684 0.09618 0.09142 -0.0339 1.0000 0.0565
-7.250 -0.3662 0.09453 0.08975 -0.0378 1.0000 0.0567
-7.000 -0.3640 0.08804 0.08340 -0.0322 1.0000 0.0577
-6.750 -0.3608 0.08434 0.07976 -0.0282 1.0000 0.0591
-6.500 -0.3587 0.08160 0.07705 -0.0268 1.0000 0.0605
-6.250 -0.3564 0.07901 0.07449 -0.0265 1.0000 0.0623
-6.000 -0.3527 0.07639 0.07189 -0.0270 1.0000 0.0644
-5.750 -0.3441 0.07386 0.06931 -0.0297 1.0000 0.0678
-5.500 -0.3218 0.07231 0.06743 -0.0384 1.0000 0.0704
-5.250 -0.3227 0.06735 0.06268 -0.0342 1.0000 0.0719
-5.000 -0.3167 0.06438 0.05976 -0.0323 1.0000 0.0743
-4.750 -0.3045 0.06159 0.05693 -0.0328 1.0000 0.0777
-4.500 -0.2698 0.06014 0.05493 -0.0399 1.0000 0.0844
-4.250 -0.2646 0.05542 0.05044 -0.0379 1.0000 0.0862
-4.000 -0.2525 0.05263 0.04767 -0.0372 1.0000 0.0899
-3.750 -0.2234 0.05045 0.04508 -0.0406 1.0000 0.0993
-3.500 -0.2124 0.04729 0.04207 -0.0396 1.0000 0.1040
-3.250 -0.1875 0.04492 0.03945 -0.0415 1.0000 0.1148
-3.000 -0.1632 0.04327 0.03752 -0.0428 1.0000 0.1277
-2.750 -0.1468 0.04038 0.03475 -0.0426 1.0000 0.1350
-2.500 -0.1209 0.03884 0.03289 -0.0442 1.0000 0.1572
-2.250 -0.0853 0.03599 0.03005 -0.0479 0.9957 0.1888
-2.000 -0.0414 0.03327 0.02746 -0.0528 0.9867 0.2535
-1.750 -0.0022 0.03102 0.02526 -0.0561 0.9787 0.3267
-1.500 0.0392 0.02863 0.02298 -0.0590 0.9720 0.3895
-1.250 0.0868 0.02670 0.02088 -0.0631 0.9627 0.4131
-1.000 0.1691 0.02586 0.01858 -0.0722 0.9545 0.2624
-0.750 0.2280 0.02464 0.01647 -0.0747 0.9454 0.1515
-0.500 0.2745 0.02363 0.01507 -0.0766 0.9349 0.1216
-0.250 0.3283 0.02282 0.01390 -0.0803 0.9279 0.1117
0.000 0.3698 0.02156 0.01263 -0.0823 0.9161 0.1095
0.250 0.4132 0.02046 0.01154 -0.0845 0.9049 0.1062
0.500 0.4568 0.01943 0.01054 -0.0865 0.8948 0.1052
0.750 0.4969 0.01846 0.00965 -0.0878 0.8832 0.1066
1.000 0.5310 0.01775 0.00894 -0.0879 0.8680 0.1127
1.250 0.5622 0.01704 0.00824 -0.0875 0.8500 0.1215
1.500 0.5919 0.01647 0.00764 -0.0867 0.8293 0.1332
1.750 0.6259 0.01399 0.00711 -0.0866 0.8098 1.0000
2.000 0.6532 0.01383 0.00660 -0.0851 0.7834 1.0000
2.250 0.6801 0.01368 0.00625 -0.0838 0.7533 1.0000
2.500 0.7069 0.01362 0.00595 -0.0825 0.7200 1.0000
2.750 0.7328 0.01375 0.00582 -0.0813 0.6846 1.0000
3.000 0.7583 0.01406 0.00589 -0.0803 0.6508 1.0000
3.250 0.7836 0.01452 0.00609 -0.0794 0.6205 1.0000
3.500 0.8088 0.01502 0.00637 -0.0786 0.5946 1.0000
3.750 0.8336 0.01549 0.00671 -0.0778 0.5708 1.0000
4.000 0.8585 0.01595 0.00704 -0.0771 0.5501 1.0000
4.250 0.8833 0.01639 0.00743 -0.0764 0.5312 1.0000
4.500 0.9088 0.01686 0.00786 -0.0759 0.5160 1.0000
4.750 0.9337 0.01729 0.00826 -0.0753 0.5003 1.0000
5.000 0.9576 0.01766 0.00860 -0.0744 0.4819 1.0000
5.250 0.9812 0.01801 0.00886 -0.0735 0.4633 1.0000
5.500 1.0052 0.01842 0.00923 -0.0727 0.4469 1.0000
5.750 1.0290 0.01885 0.00969 -0.0720 0.4310 1.0000
6.000 1.0527 0.01928 0.01016 -0.0712 0.4157 1.0000
6.250 1.0751 0.01966 0.01061 -0.0702 0.3979 1.0000
6.500 1.0971 0.02001 0.01103 -0.0691 0.3792 1.0000
6.750 1.1187 0.02034 0.01145 -0.0680 0.3606 1.0000
7.000 1.1394 0.02065 0.01181 -0.0667 0.3403 1.0000
7.250 1.1573 0.02083 0.01209 -0.0649 0.3111 1.0000
7.500 1.1740 0.02100 0.01240 -0.0629 0.2588 1.0000
7.750 1.1821 0.02261 0.01325 -0.0601 0.1478 1.0000
8.000 1.1930 0.02452 0.01484 -0.0578 0.1097 1.0000
8.250 1.2059 0.02605 0.01630 -0.0557 0.0973 1.0000
8.500 1.2162 0.02767 0.01787 -0.0533 0.0895 1.0000
8.750 1.2294 0.02905 0.01938 -0.0511 0.0849 1.0000
9.000 1.2412 0.03060 0.02095 -0.0489 0.0806 1.0000
9.250 1.2538 0.03260 0.02287 -0.0469 0.0765 1.0000
9.500 1.2724 0.03424 0.02466 -0.0455 0.0731 1.0000
9.750 1.2935 0.03619 0.02667 -0.0445 0.0699 1.0000
10.000 1.3235 0.03971 0.02999 -0.0453 0.0655 1.0000
10.250 1.3421 0.04185 0.03247 -0.0439 0.0639 1.0000
10.500 1.3596 0.04447 0.03548 -0.0424 0.0625 1.0000
10.750 1.3720 0.04713 0.03850 -0.0406 0.0606 1.0000
11.000 1.3822 0.04995 0.04162 -0.0387 0.0587 1.0000
11.250 1.3884 0.05325 0.04528 -0.0365 0.0581 1.0000
11.500 1.3874 0.05677 0.04922 -0.0337 0.0581 1.0000
11.750 1.3786 0.06033 0.05320 -0.0304 0.0585 1.0000
12.000 1.3632 0.06377 0.05700 -0.0267 0.0588 1.0000
12.250 1.3442 0.06747 0.06102 -0.0237 0.0592 1.0000
12.500 1.3225 0.07162 0.06547 -0.0217 0.0597 1.0000
12.750 1.2986 0.07633 0.07046 -0.0208 0.0603 1.0000
13.000 1.2728 0.08173 0.07611 -0.0213 0.0610 1.0000
13.250 1.2458 0.08795 0.08255 -0.0231 0.0617 1.0000
13.500 1.2181 0.09507 0.08985 -0.0264 0.0625 1.0000
13.750 1.1901 0.10312 0.09806 -0.0308 0.0633 1.0000
14.000 1.1642 0.11183 0.10687 -0.0358 0.0642 1.0000
14.250 1.1564 0.11904 0.11410 -0.0374 0.0653 1.0000
14.500 0.8034 0.14564 0.14088 -0.0458 0.0874 1.0000
14.750 0.8050 0.14959 0.14487 -0.0463 0.0900 1.0000
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Polar data table (+)
Polar graphs
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