GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Reynolds number: 50,000 Max Cl/Cd: 36.91 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe276-il-50000.txt Download as CSV file: xf-goe276-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4103 0.10832 0.10158 -0.0186 1.0000 0.1333
-7.750 -0.3939 0.10250 0.09577 -0.0161 1.0000 0.1394
-7.500 -0.3950 0.10042 0.09377 -0.0175 1.0000 0.1464
-7.250 -0.3942 0.09749 0.09093 -0.0197 1.0000 0.1508
-7.000 -0.3879 0.09448 0.08796 -0.0195 1.0000 0.1615
-6.500 -0.3817 0.08983 0.08345 -0.0268 1.0000 0.1789
-6.250 -0.3726 0.08529 0.07897 -0.0214 1.0000 0.1913
-6.000 -0.3657 0.08185 0.07559 -0.0204 1.0000 0.2018
-5.750 -0.3595 0.07883 0.07264 -0.0209 1.0000 0.2152
-5.500 -0.3526 0.07589 0.06975 -0.0208 1.0000 0.2313
-5.250 -0.3444 0.07363 0.06750 -0.0247 1.0000 0.2544
-4.750 -0.3338 0.06749 0.06151 -0.0176 1.0000 0.3034
-4.500 -0.3290 0.06530 0.05937 -0.0162 1.0000 0.3446
-4.250 0.0089 0.04114 0.03425 -0.0230 1.0000 1.0000
-4.000 0.0196 0.03929 0.03247 -0.0237 1.0000 1.0000
-3.750 0.0301 0.03753 0.03077 -0.0243 1.0000 1.0000
-3.500 0.0400 0.03586 0.02917 -0.0248 1.0000 1.0000
-3.250 0.0061 0.03639 0.02989 -0.0150 1.0000 0.9825
-3.000 -0.0442 0.03729 0.03105 -0.0022 1.0000 0.9515
-2.750 -0.0934 0.03791 0.03194 0.0096 1.0000 0.9267
-2.500 -0.1379 0.03794 0.03223 0.0196 1.0000 0.9008
-2.250 -0.1850 0.03788 0.03240 0.0302 1.0000 0.8848
-2.000 -0.0227 0.03468 0.02667 -0.0554 1.0000 0.2773
-1.750 0.0242 0.03271 0.02377 -0.0592 1.0000 0.2222
-1.500 0.0568 0.03103 0.02171 -0.0602 1.0000 0.2036
-1.250 0.0891 0.02972 0.01996 -0.0608 1.0000 0.1864
-1.000 0.1196 0.02877 0.01860 -0.0611 1.0000 0.1748
-0.750 0.1489 0.02793 0.01741 -0.0612 1.0000 0.1669
-0.500 0.1762 0.02745 0.01665 -0.0611 1.0000 0.1624
-0.250 0.2018 0.02693 0.01602 -0.0609 1.0000 0.1617
0.000 0.2271 0.02671 0.01563 -0.0607 1.0000 0.1642
0.250 0.2520 0.02646 0.01535 -0.0607 1.0000 0.1670
0.500 0.2753 0.02654 0.01542 -0.0608 1.0000 0.1685
0.750 0.2964 0.02697 0.01588 -0.0611 1.0000 0.1714
1.000 0.3606 0.02698 0.01593 -0.0693 0.9825 0.1831
1.250 0.4318 0.02441 0.01568 -0.0779 0.9572 0.8834
1.500 0.5042 0.02426 0.01491 -0.0853 0.9202 1.0000
1.750 0.5764 0.02375 0.01401 -0.0924 0.8894 1.0000
2.000 0.6345 0.02317 0.01325 -0.0964 0.8586 1.0000
2.250 0.6779 0.02286 0.01283 -0.0978 0.8263 1.0000
2.500 0.7134 0.02273 0.01259 -0.0978 0.7957 1.0000
2.750 0.7463 0.02266 0.01241 -0.0973 0.7683 1.0000
3.000 0.7749 0.02280 0.01247 -0.0964 0.7417 1.0000
3.250 0.8023 0.02305 0.01268 -0.0955 0.7165 1.0000
3.500 0.8313 0.02324 0.01278 -0.0946 0.6946 1.0000
3.750 0.8578 0.02367 0.01317 -0.0938 0.6720 1.0000
4.000 0.8860 0.02406 0.01350 -0.0929 0.6520 1.0000
4.250 0.9111 0.02477 0.01423 -0.0921 0.6304 1.0000
4.500 0.9378 0.02541 0.01481 -0.0913 0.6104 1.0000
4.750 0.9623 0.02621 0.01561 -0.0903 0.5886 1.0000
5.000 0.9873 0.02688 0.01626 -0.0890 0.5660 1.0000
5.250 1.0105 0.02774 0.01714 -0.0878 0.5431 1.0000
5.500 1.0351 0.02858 0.01796 -0.0867 0.5222 1.0000
5.750 1.0593 0.02962 0.01905 -0.0857 0.5032 1.0000
6.000 1.0818 0.03088 0.02050 -0.0848 0.4841 1.0000
6.250 1.1049 0.03215 0.02187 -0.0839 0.4657 1.0000
6.500 1.1286 0.03342 0.02321 -0.0829 0.4476 1.0000
6.750 1.1509 0.03487 0.02478 -0.0818 0.4297 1.0000
7.000 1.1703 0.03667 0.02688 -0.0807 0.4125 1.0000
7.250 1.1900 0.03859 0.02907 -0.0796 0.3970 1.0000
7.500 1.2093 0.04057 0.03130 -0.0785 0.3826 1.0000
7.750 1.2286 0.04247 0.03344 -0.0773 0.3688 1.0000
8.000 1.2504 0.04420 0.03538 -0.0763 0.3562 1.0000
8.250 1.2664 0.04580 0.03732 -0.0746 0.3405 1.0000
8.500 1.2874 0.04347 0.03499 -0.0716 0.3074 1.0000
8.750 1.3098 0.03911 0.03025 -0.0683 0.2671 1.0000
9.000 1.3195 0.03821 0.02938 -0.0648 0.2311 1.0000
9.250 1.3150 0.03893 0.02984 -0.0596 0.1769 1.0000
9.500 1.3127 0.04163 0.03216 -0.0553 0.1372 1.0000
9.750 1.3200 0.04445 0.03462 -0.0527 0.1171 1.0000
10.000 1.3310 0.04740 0.03758 -0.0506 0.1039 1.0000
10.250 1.3404 0.05075 0.04144 -0.0483 0.0967 1.0000
10.500 1.3594 0.05423 0.04482 -0.0473 0.0907 1.0000
10.750 1.3592 0.05802 0.04922 -0.0445 0.0880 1.0000
11.000 1.3558 0.06185 0.05349 -0.0418 0.0856 1.0000
11.250 1.3507 0.06548 0.05744 -0.0393 0.0833 1.0000
11.500 1.3463 0.06882 0.06095 -0.0368 0.0812 1.0000
11.750 1.3498 0.07283 0.06496 -0.0355 0.0788 1.0000
12.000 1.3305 0.07716 0.06960 -0.0332 0.0788 1.0000
12.250 1.3100 0.08201 0.07471 -0.0321 0.0789 1.0000
12.500 1.2213 0.09441 0.08785 -0.0382 0.0873 1.0000
12.750 1.1928 0.10319 0.09675 -0.0428 0.0891 1.0000
13.000 1.1691 0.11221 0.10582 -0.0477 0.0903 1.0000
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Polar data table (+)
Polar graphs
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