GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Reynolds number: 50,000 Max Cl/Cd: 41.08 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe280-il-50000-n5.txt Download as CSV file: xf-goe280-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 280 (DAIMLER XI) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3241 0.10090 0.09462 -0.0236 1.0000 0.0615
-7.250 -0.3243 0.09864 0.09247 -0.0248 1.0000 0.0634
-7.000 -0.3244 0.09685 0.09077 -0.0276 1.0000 0.0651
-6.750 -0.3217 0.09536 0.08933 -0.0321 1.0000 0.0661
-6.500 -0.3148 0.09366 0.08762 -0.0367 1.0000 0.0666
-6.250 -0.3141 0.08776 0.08187 -0.0306 1.0000 0.0685
-6.000 -0.3102 0.08450 0.07867 -0.0288 1.0000 0.0714
-5.750 -0.3045 0.08169 0.07590 -0.0294 1.0000 0.0749
-5.500 -0.2880 0.08003 0.07411 -0.0367 1.0000 0.0808
-5.250 -0.2842 0.07582 0.07002 -0.0350 1.0000 0.0833
-5.000 -0.2784 0.07281 0.06706 -0.0334 1.0000 0.0900
-4.750 -0.2615 0.06977 0.06394 -0.0375 1.0000 0.0979
-4.250 -0.2373 0.06363 0.05778 -0.0385 1.0000 0.1151
-4.000 -0.2198 0.06069 0.05475 -0.0406 1.0000 0.1281
-3.750 -0.2042 0.05781 0.05181 -0.0415 1.0000 0.1435
-3.500 -0.1809 0.05479 0.04869 -0.0442 0.9979 0.1718
-3.250 -0.1548 0.05115 0.04512 -0.0464 0.9909 0.2321
-2.750 -0.0147 0.04269 0.03493 -0.0644 0.9776 0.0941
-2.500 0.0283 0.03939 0.03127 -0.0683 0.9698 0.0906
-2.250 0.0780 0.03677 0.02791 -0.0720 0.9623 0.0795
-2.000 0.1218 0.03422 0.02496 -0.0754 0.9544 0.0765
-1.750 0.1650 0.03277 0.02287 -0.0780 0.9448 0.0806
-1.500 0.2105 0.03084 0.02055 -0.0813 0.9376 0.0796
-1.250 0.2500 0.02940 0.01878 -0.0834 0.9270 0.0786
-1.000 0.2898 0.02819 0.01728 -0.0853 0.9164 0.0781
-0.750 0.3306 0.02711 0.01593 -0.0873 0.9064 0.0781
-0.500 0.3708 0.02622 0.01478 -0.0889 0.8960 0.0795
-0.250 0.4057 0.02542 0.01388 -0.0899 0.8829 0.0861
0.000 0.4399 0.02476 0.01310 -0.0906 0.8690 0.0901
0.250 0.4735 0.02420 0.01240 -0.0911 0.8545 0.0917
0.500 0.5066 0.02371 0.01176 -0.0915 0.8395 0.0938
0.750 0.5362 0.02337 0.01133 -0.0914 0.8216 0.0964
1.000 0.5670 0.02299 0.01089 -0.0915 0.8041 0.1011
1.250 0.5983 0.02265 0.01048 -0.0915 0.7867 0.1093
1.750 0.6529 0.02025 0.00987 -0.0897 0.7519 1.0000
2.000 0.6810 0.02033 0.00969 -0.0890 0.7316 1.0000
2.250 0.7094 0.02041 0.00952 -0.0883 0.7117 1.0000
2.500 0.7365 0.02057 0.00947 -0.0876 0.6906 1.0000
2.750 0.7628 0.02078 0.00953 -0.0868 0.6685 1.0000
3.000 0.7887 0.02102 0.00964 -0.0860 0.6464 1.0000
3.250 0.8140 0.02127 0.00978 -0.0852 0.6237 1.0000
3.500 0.8388 0.02154 0.00994 -0.0843 0.5998 1.0000
3.750 0.8636 0.02180 0.01008 -0.0832 0.5757 1.0000
4.000 0.8876 0.02212 0.01028 -0.0822 0.5503 1.0000
4.250 0.9112 0.02250 0.01055 -0.0812 0.5249 1.0000
4.500 0.9349 0.02293 0.01091 -0.0803 0.5008 1.0000
4.750 0.9581 0.02340 0.01134 -0.0794 0.4770 1.0000
5.000 0.9812 0.02391 0.01184 -0.0786 0.4539 1.0000
5.250 1.0041 0.02444 0.01236 -0.0777 0.4317 1.0000
5.500 1.0266 0.02500 0.01301 -0.0769 0.4092 1.0000
5.750 1.0489 0.02560 0.01361 -0.0760 0.3879 1.0000
6.000 1.0708 0.02624 0.01430 -0.0751 0.3667 1.0000
6.250 1.0924 0.02693 0.01502 -0.0742 0.3466 1.0000
6.500 1.1136 0.02766 0.01579 -0.0733 0.3283 1.0000
6.750 1.1307 0.02840 0.01647 -0.0719 0.3010 1.0000
7.000 1.1442 0.02924 0.01711 -0.0701 0.2660 1.0000
7.250 1.1606 0.03015 0.01795 -0.0689 0.2427 1.0000
7.500 1.1774 0.03110 0.01888 -0.0676 0.2230 1.0000
7.750 1.1948 0.03205 0.01996 -0.0665 0.2087 1.0000
8.000 1.2112 0.03305 0.02104 -0.0653 0.1928 1.0000
8.250 1.2271 0.03409 0.02217 -0.0640 0.1800 1.0000
8.500 1.2437 0.03510 0.02339 -0.0627 0.1709 1.0000
8.750 1.2589 0.03617 0.02463 -0.0613 0.1602 1.0000
9.000 1.2713 0.03738 0.02595 -0.0598 0.1460 1.0000
9.250 1.2816 0.03873 0.02736 -0.0580 0.1297 1.0000
9.500 1.2927 0.03996 0.02881 -0.0562 0.1218 1.0000
9.750 1.3023 0.04131 0.03046 -0.0543 0.1139 1.0000
10.000 1.3134 0.04266 0.03213 -0.0526 0.1034 1.0000
10.750 1.2878 0.05293 0.04190 -0.0472 0.0264 1.0000
11.000 1.2812 0.05664 0.04580 -0.0465 0.0254 1.0000
11.250 1.2735 0.06072 0.05010 -0.0463 0.0246 1.0000
11.500 1.2645 0.06525 0.05487 -0.0468 0.0241 1.0000
11.750 1.2544 0.07021 0.06008 -0.0479 0.0238 1.0000
12.000 1.2429 0.07569 0.06582 -0.0495 0.0236 1.0000
12.250 1.2306 0.08157 0.07195 -0.0515 0.0235 1.0000
12.500 1.2173 0.08787 0.07850 -0.0540 0.0234 1.0000
12.750 1.2036 0.09441 0.08529 -0.0566 0.0234 1.0000
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Polar data table (+)
Polar graphs
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