GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Reynolds number: 100,000 Max Cl/Cd: 58.98 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe281-il-100000.txt Download as CSV file: xf-goe281-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 281 (DAIMLER XII) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3337 0.09715 0.09249 -0.0267 1.0000 0.0544
-7.500 -0.3402 0.09582 0.09126 -0.0281 1.0000 0.0553
-7.250 -0.3427 0.09457 0.09009 -0.0326 1.0000 0.0560
-7.000 -0.3402 0.09297 0.08850 -0.0377 1.0000 0.0564
-6.750 -0.3397 0.08801 0.08363 -0.0352 1.0000 0.0572
-6.500 -0.3384 0.08405 0.07974 -0.0292 1.0000 0.0589
-6.250 -0.3365 0.08140 0.07712 -0.0276 1.0000 0.0607
-6.000 -0.3342 0.07888 0.07465 -0.0274 1.0000 0.0629
-5.750 -0.3302 0.07633 0.07212 -0.0285 1.0000 0.0656
-5.500 -0.3080 0.07475 0.07030 -0.0389 1.0000 0.0699
-5.250 -0.3050 0.07038 0.06599 -0.0382 1.0000 0.0711
-5.000 -0.3075 0.06748 0.06324 -0.0335 1.0000 0.0733
-4.750 -0.3012 0.06517 0.06094 -0.0327 1.0000 0.0777
-4.500 -0.2725 0.06219 0.05764 -0.0407 1.0000 0.0851
-4.250 -0.2712 0.05919 0.05480 -0.0377 1.0000 0.0874
-4.000 -0.2603 0.05696 0.05255 -0.0375 1.0000 0.0927
-3.750 -0.2168 0.05274 0.04811 -0.0449 0.9950 0.1038
-3.500 -0.1706 0.04893 0.04411 -0.0518 0.9878 0.1195
-3.250 -0.1225 0.04546 0.04040 -0.0589 0.9811 0.1460
-3.000 -0.0800 0.04244 0.03723 -0.0641 0.9732 0.1752
-2.750 -0.0408 0.03979 0.03454 -0.0679 0.9656 0.2100
-1.500 0.1966 0.02762 0.02070 -0.0901 0.9306 0.2248
-1.250 0.2617 0.02555 0.01735 -0.0935 0.9270 0.1256
-1.000 0.3001 0.02476 0.01610 -0.0945 0.9167 0.1133
-0.750 0.3495 0.02279 0.01402 -0.0981 0.9127 0.1050
-0.500 0.3843 0.02227 0.01324 -0.0986 0.9017 0.0991
-0.250 0.4211 0.02128 0.01222 -0.0998 0.8925 0.0972
0.000 0.4612 0.02024 0.01120 -0.1014 0.8852 0.0963
0.250 0.4924 0.01961 0.01061 -0.1014 0.8737 0.0972
0.500 0.5240 0.01894 0.00999 -0.1016 0.8629 0.1027
0.750 0.5576 0.01838 0.00938 -0.1018 0.8528 0.1074
1.250 0.6200 0.01739 0.00833 -0.1010 0.8270 0.1339
1.500 0.6474 0.01519 0.00798 -0.0997 0.8116 1.0000
1.750 0.6728 0.01513 0.00770 -0.0981 0.7925 1.0000
2.000 0.6992 0.01510 0.00746 -0.0969 0.7747 1.0000
2.250 0.7257 0.01512 0.00733 -0.0959 0.7577 1.0000
2.500 0.7522 0.01518 0.00724 -0.0949 0.7406 1.0000
2.750 0.7778 0.01531 0.00725 -0.0940 0.7218 1.0000
3.000 0.8034 0.01547 0.00731 -0.0930 0.7024 1.0000
3.250 0.8295 0.01564 0.00736 -0.0922 0.6840 1.0000
3.500 0.8555 0.01586 0.00749 -0.0914 0.6657 1.0000
3.750 0.8805 0.01614 0.00772 -0.0906 0.6453 1.0000
4.000 0.9060 0.01638 0.00787 -0.0897 0.6256 1.0000
4.250 0.9307 0.01663 0.00804 -0.0888 0.6043 1.0000
4.500 0.9551 0.01683 0.00821 -0.0878 0.5816 1.0000
4.750 0.9791 0.01703 0.00839 -0.0868 0.5584 1.0000
5.000 1.0035 0.01725 0.00856 -0.0859 0.5367 1.0000
5.250 1.0275 0.01752 0.00883 -0.0850 0.5142 1.0000
5.500 1.0517 0.01783 0.00909 -0.0841 0.4924 1.0000
5.750 1.0749 0.01825 0.00948 -0.0832 0.4680 1.0000
6.000 1.0979 0.01880 0.00993 -0.0822 0.4433 1.0000
6.250 1.1194 0.01938 0.01039 -0.0810 0.4154 1.0000
6.500 1.1398 0.01991 0.01089 -0.0797 0.3865 1.0000
6.750 1.1597 0.02037 0.01134 -0.0784 0.3582 1.0000
7.000 1.1793 0.02079 0.01176 -0.0771 0.3306 1.0000
7.250 1.1996 0.02129 0.01231 -0.0759 0.3066 1.0000
7.500 1.2186 0.02184 0.01285 -0.0746 0.2808 1.0000
7.750 1.2362 0.02249 0.01347 -0.0732 0.2531 1.0000
8.000 1.2546 0.02323 0.01420 -0.0718 0.2335 1.0000
8.250 1.2726 0.02395 0.01494 -0.0705 0.2078 1.0000
8.500 1.2901 0.02473 0.01569 -0.0691 0.1773 1.0000
8.750 1.3064 0.02570 0.01655 -0.0675 0.1377 1.0000
9.000 1.3165 0.02733 0.01785 -0.0652 0.0863 1.0000
9.250 1.3214 0.02941 0.01960 -0.0623 0.0541 1.0000
9.500 1.3292 0.03109 0.02133 -0.0596 0.0487 1.0000
9.750 1.3347 0.03275 0.02313 -0.0567 0.0457 1.0000
10.000 1.3347 0.03463 0.02513 -0.0532 0.0434 1.0000
10.250 1.3321 0.03677 0.02741 -0.0499 0.0417 1.0000
10.500 1.3331 0.03875 0.02960 -0.0473 0.0404 1.0000
10.750 1.3327 0.04097 0.03200 -0.0449 0.0394 1.0000
11.000 1.3319 0.04335 0.03455 -0.0427 0.0389 1.0000
11.250 1.3318 0.04584 0.03719 -0.0408 0.0384 1.0000
11.500 1.3334 0.04834 0.03985 -0.0391 0.0380 1.0000
11.750 1.3379 0.05076 0.04239 -0.0374 0.0377 1.0000
12.000 1.3464 0.05307 0.04481 -0.0357 0.0375 1.0000
12.250 1.3588 0.05536 0.04725 -0.0340 0.0374 1.0000
12.500 1.3727 0.05791 0.04999 -0.0324 0.0375 1.0000
12.750 1.3811 0.06094 0.05327 -0.0310 0.0376 1.0000
13.000 1.3835 0.06434 0.05694 -0.0298 0.0374 1.0000
13.250 1.3807 0.06807 0.06093 -0.0289 0.0372 1.0000
13.500 1.3740 0.07217 0.06534 -0.0285 0.0370 1.0000
13.750 1.3632 0.07670 0.07016 -0.0285 0.0370 1.0000
14.000 1.3488 0.08179 0.07553 -0.0292 0.0372 1.0000
14.250 1.3314 0.08743 0.08146 -0.0306 0.0375 1.0000
14.500 1.3115 0.09369 0.08799 -0.0329 0.0378 1.0000
14.750 1.2897 0.10059 0.09515 -0.0361 0.0382 1.0000
15.000 1.2665 0.10826 0.10302 -0.0402 0.0386 1.0000
15.250 1.2424 0.11684 0.11182 -0.0454 0.0392 1.0000
15.500 1.2176 0.12633 0.12150 -0.0515 0.0398 1.0000
15.750 1.1930 0.13655 0.13187 -0.0582 0.0406 1.0000
16.000 1.1709 0.14695 0.14235 -0.0648 0.0414 1.0000
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Polar data table (+)
Polar graphs
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