GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Reynolds number: 100,000 Max Cl/Cd: 53.05 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe276-il-100000.txt Download as CSV file: xf-goe276-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 276 (DAIMLER VII) 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 -0.3792 0.09699 0.09211 -0.0188 1.0000 0.0549
-7.500 -0.3786 0.09438 0.08958 -0.0193 1.0000 0.0569
-7.250 -0.3756 0.09169 0.08695 -0.0215 1.0000 0.0592
-7.000 -0.3695 0.08966 0.08495 -0.0286 1.0000 0.0614
-6.750 -0.3537 0.08791 0.08309 -0.0398 1.0000 0.0622
-6.500 -0.3526 0.08199 0.07731 -0.0356 1.0000 0.0633
-6.250 -0.3493 0.07831 0.07371 -0.0313 1.0000 0.0650
-6.000 -0.3419 0.07526 0.07069 -0.0307 1.0000 0.0672
-5.750 -0.3319 0.07220 0.06763 -0.0321 1.0000 0.0702
-5.500 -0.2971 0.07010 0.06515 -0.0446 1.0000 0.0761
-5.250 -0.2922 0.06509 0.06027 -0.0431 1.0000 0.0775
-5.000 -0.2896 0.06203 0.05733 -0.0395 1.0000 0.0801
-4.750 -0.2750 0.05934 0.05460 -0.0402 1.0000 0.0864
-4.500 -0.2500 0.05561 0.05065 -0.0448 1.0000 0.0928
-4.250 -0.2380 0.05295 0.04801 -0.0437 1.0000 0.0974
-4.000 -0.2100 0.04969 0.04450 -0.0476 1.0000 0.1071
-3.750 -0.1937 0.04725 0.04206 -0.0473 1.0000 0.1148
-3.500 -0.1717 0.04444 0.03913 -0.0487 1.0000 0.1257
-3.250 -0.1441 0.04240 0.03679 -0.0513 1.0000 0.1502
-3.000 -0.1263 0.03988 0.03431 -0.0512 1.0000 0.1671
-2.750 -0.1043 0.03804 0.03238 -0.0518 1.0000 0.1960
-2.500 -0.0855 0.03610 0.03050 -0.0515 1.0000 0.2274
-1.750 -0.0382 0.03142 0.02623 -0.0465 1.0000 0.4049
-1.500 -0.0247 0.02954 0.02460 -0.0431 1.0000 0.4683
-1.250 -0.0031 0.02784 0.02300 -0.0416 1.0000 0.5254
-0.750 0.1861 0.02411 0.01578 -0.0666 0.9886 0.1290
-0.500 0.2399 0.02294 0.01426 -0.0707 0.9801 0.1149
-0.250 0.2943 0.02207 0.01307 -0.0750 0.9705 0.1055
0.000 0.3457 0.02085 0.01183 -0.0792 0.9594 0.1032
0.250 0.3963 0.01970 0.01072 -0.0831 0.9466 0.1032
0.500 0.4482 0.01839 0.00959 -0.0872 0.9333 0.1098
0.750 0.5017 0.01724 0.00847 -0.0912 0.9185 0.1147
1.000 0.5491 0.01629 0.00749 -0.0937 0.8976 0.1241
1.250 0.5905 0.01414 0.00689 -0.0955 0.8735 0.6464
1.500 0.6181 0.01327 0.00625 -0.0931 0.8355 1.0000
1.750 0.6464 0.01316 0.00583 -0.0917 0.7885 1.0000
2.000 0.6727 0.01318 0.00556 -0.0903 0.7348 1.0000
2.250 0.6988 0.01337 0.00538 -0.0891 0.6860 1.0000
2.500 0.7249 0.01372 0.00538 -0.0881 0.6483 1.0000
2.750 0.7511 0.01417 0.00554 -0.0875 0.6191 1.0000
3.000 0.7774 0.01466 0.00582 -0.0870 0.5954 1.0000
3.250 0.8037 0.01515 0.00615 -0.0866 0.5736 1.0000
3.500 0.8299 0.01565 0.00649 -0.0861 0.5533 1.0000
3.750 0.8560 0.01616 0.00685 -0.0857 0.5348 1.0000
4.000 0.8819 0.01665 0.00729 -0.0852 0.5160 1.0000
4.250 0.9075 0.01716 0.00773 -0.0848 0.4976 1.0000
4.500 0.9333 0.01770 0.00820 -0.0843 0.4807 1.0000
4.750 0.9592 0.01828 0.00873 -0.0840 0.4650 1.0000
5.000 0.9850 0.01888 0.00934 -0.0836 0.4498 1.0000
5.250 1.0105 0.01950 0.00996 -0.0832 0.4347 1.0000
5.500 1.0360 0.02013 0.01061 -0.0828 0.4197 1.0000
5.750 1.0612 0.02076 0.01133 -0.0823 0.4051 1.0000
6.000 1.0862 0.02139 0.01203 -0.0818 0.3905 1.0000
6.250 1.1109 0.02199 0.01273 -0.0812 0.3758 1.0000
6.500 1.1353 0.02257 0.01340 -0.0806 0.3609 1.0000
6.750 1.1594 0.02312 0.01409 -0.0799 0.3457 1.0000
7.000 1.1829 0.02348 0.01451 -0.0790 0.3291 1.0000
7.250 1.2045 0.02360 0.01471 -0.0778 0.3094 1.0000
7.500 1.2252 0.02367 0.01488 -0.0765 0.2887 1.0000
7.750 1.2454 0.02383 0.01505 -0.0752 0.2686 1.0000
8.000 1.2641 0.02402 0.01539 -0.0738 0.2447 1.0000
8.250 1.2826 0.02435 0.01585 -0.0724 0.2195 1.0000
8.500 1.2999 0.02476 0.01635 -0.0708 0.1801 1.0000
8.750 1.3056 0.02713 0.01813 -0.0679 0.0933 1.0000
9.000 1.3133 0.02943 0.02011 -0.0651 0.0677 1.0000
9.250 1.3216 0.03138 0.02211 -0.0624 0.0587 1.0000
9.500 1.3281 0.03338 0.02423 -0.0594 0.0539 1.0000
9.750 1.3354 0.03527 0.02626 -0.0566 0.0509 1.0000
10.000 1.3418 0.03732 0.02836 -0.0537 0.0485 1.0000
10.250 1.3499 0.03992 0.03094 -0.0512 0.0466 1.0000
10.500 1.3652 0.04255 0.03370 -0.0495 0.0452 1.0000
10.750 1.3769 0.04477 0.03618 -0.0475 0.0435 1.0000
11.000 1.3862 0.04716 0.03882 -0.0453 0.0418 1.0000
11.250 1.3950 0.04989 0.04182 -0.0433 0.0407 1.0000
11.500 1.4007 0.05297 0.04518 -0.0410 0.0402 1.0000
11.750 1.4009 0.05622 0.04874 -0.0384 0.0400 1.0000
12.000 1.3955 0.05968 0.05253 -0.0357 0.0400 1.0000
12.250 1.3845 0.06342 0.05661 -0.0332 0.0402 1.0000
12.500 1.3694 0.06755 0.06108 -0.0315 0.0404 1.0000
12.750 1.3510 0.07219 0.06603 -0.0306 0.0406 1.0000
13.000 1.3301 0.07742 0.07156 -0.0309 0.0409 1.0000
13.250 1.3071 0.08338 0.07780 -0.0324 0.0413 1.0000
13.500 1.2825 0.09023 0.08491 -0.0355 0.0416 1.0000
13.750 1.2562 0.09812 0.09303 -0.0400 0.0421 1.0000
14.000 1.2284 0.10719 0.10231 -0.0460 0.0425 1.0000
14.250 1.1987 0.11751 0.11280 -0.0531 0.0431 1.0000
14.500 1.1679 0.12909 0.12447 -0.0611 0.0439 1.0000
14.750 1.1396 0.14122 0.13666 -0.0690 0.0448 1.0000
15.000 1.1211 0.15153 0.14697 -0.0747 0.0457 1.0000
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Polar data table (+)
Polar graphs
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