GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Reynolds number: 100,000 Max Cl/Cd: 55.54 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe280-il-100000.txt Download as CSV file: xf-goe280-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3340 0.09563 0.09108 -0.0216 1.0000 0.0451
-7.250 -0.3339 0.09320 0.08872 -0.0225 1.0000 0.0464
-7.000 -0.3324 0.09086 0.08645 -0.0246 1.0000 0.0476
-6.750 -0.3291 0.08892 0.08456 -0.0284 1.0000 0.0486
-6.500 -0.3210 0.08735 0.08296 -0.0340 1.0000 0.0493
-6.250 -0.3099 0.08559 0.08110 -0.0383 1.0000 0.0496
-6.000 -0.3082 0.08022 0.07584 -0.0366 1.0000 0.0503
-5.750 -0.3092 0.07597 0.07171 -0.0323 1.0000 0.0515
-5.500 -0.3049 0.07290 0.06869 -0.0308 1.0000 0.0530
-5.250 -0.2969 0.07001 0.06580 -0.0309 1.0000 0.0550
-5.000 -0.2852 0.06708 0.06283 -0.0322 1.0000 0.0576
-4.750 -0.2522 0.06553 0.06093 -0.0392 1.0000 0.0626
-4.500 -0.2385 0.06134 0.05669 -0.0406 1.0000 0.0640
-4.250 -0.2359 0.05768 0.05319 -0.0382 1.0000 0.0665
-4.000 -0.2219 0.05519 0.05067 -0.0385 1.0000 0.0723
-3.750 -0.1945 0.05241 0.04760 -0.0421 1.0000 0.0791
-3.500 -0.1831 0.04963 0.04489 -0.0414 1.0000 0.0835
-3.250 -0.1552 0.04746 0.04239 -0.0442 1.0000 0.0932
-3.000 -0.1405 0.04489 0.03986 -0.0441 1.0000 0.1002
-2.750 -0.0881 0.04159 0.03618 -0.0512 0.9944 0.1224
-2.500 -0.0462 0.03838 0.03291 -0.0562 0.9875 0.1542
-1.750 0.0700 0.02994 0.02467 -0.0669 0.9671 0.3782
-1.500 0.1090 0.02743 0.02228 -0.0687 0.9587 0.4496
-1.250 0.1832 0.02547 0.01949 -0.0785 0.9504 0.3860
-1.000 0.2675 0.02501 0.01727 -0.0842 0.9424 0.1585
-0.750 0.3167 0.02365 0.01545 -0.0866 0.9320 0.1277
-0.500 0.3741 0.02215 0.01361 -0.0909 0.9264 0.1113
-0.250 0.4174 0.02130 0.01254 -0.0927 0.9138 0.1048
0.000 0.4579 0.02018 0.01141 -0.0943 0.9006 0.1042
0.250 0.4951 0.01914 0.01042 -0.0951 0.8862 0.1075
0.500 0.5287 0.01827 0.00958 -0.0951 0.8704 0.1077
0.750 0.5581 0.01761 0.00888 -0.0942 0.8515 0.1092
1.000 0.5864 0.01709 0.00829 -0.0932 0.8306 0.1127
1.250 0.6149 0.01665 0.00771 -0.0921 0.8104 0.1193
1.500 0.6420 0.01626 0.00730 -0.0909 0.7873 0.1379
1.750 0.6630 0.01418 0.00699 -0.0883 0.7655 1.0000
2.000 0.6893 0.01420 0.00664 -0.0867 0.7411 1.0000
2.250 0.7145 0.01433 0.00649 -0.0854 0.7137 1.0000
2.500 0.7396 0.01452 0.00644 -0.0842 0.6862 1.0000
2.750 0.7649 0.01473 0.00646 -0.0833 0.6598 1.0000
3.000 0.7905 0.01496 0.00652 -0.0825 0.6359 1.0000
3.250 0.8161 0.01520 0.00661 -0.0817 0.6122 1.0000
3.500 0.8415 0.01546 0.00678 -0.0810 0.5881 1.0000
3.750 0.8669 0.01577 0.00693 -0.0803 0.5652 1.0000
4.000 0.8922 0.01612 0.00716 -0.0797 0.5414 1.0000
4.250 0.9172 0.01652 0.00746 -0.0790 0.5172 1.0000
4.500 0.9419 0.01696 0.00781 -0.0783 0.4929 1.0000
4.750 0.9662 0.01741 0.00816 -0.0776 0.4668 1.0000
5.000 0.9901 0.01786 0.00854 -0.0769 0.4388 1.0000
5.250 1.0135 0.01836 0.00894 -0.0760 0.4097 1.0000
5.500 1.0366 0.01894 0.00942 -0.0752 0.3804 1.0000
5.750 1.0583 0.01946 0.00982 -0.0742 0.3480 1.0000
6.000 1.0792 0.01992 0.01014 -0.0733 0.3147 1.0000
6.250 1.1012 0.02057 0.01066 -0.0725 0.2922 1.0000
6.500 1.1236 0.02119 0.01128 -0.0718 0.2722 1.0000
6.750 1.1449 0.02177 0.01177 -0.0710 0.2529 1.0000
7.000 1.1663 0.02231 0.01228 -0.0703 0.2329 1.0000
7.250 1.1882 0.02292 0.01289 -0.0696 0.2195 1.0000
7.500 1.2098 0.02353 0.01351 -0.0689 0.2064 1.0000
7.750 1.2309 0.02411 0.01416 -0.0681 0.1921 1.0000
8.000 1.2519 0.02475 0.01484 -0.0673 0.1818 1.0000
8.250 1.2742 0.02533 0.01559 -0.0665 0.1737 1.0000
8.500 1.2948 0.02595 0.01630 -0.0656 0.1639 1.0000
8.750 1.3147 0.02661 0.01701 -0.0647 0.1532 1.0000
9.000 1.3345 0.02726 0.01780 -0.0637 0.1411 1.0000
9.250 1.3542 0.02796 0.01862 -0.0626 0.1290 1.0000
9.500 1.3736 0.02870 0.01955 -0.0614 0.1192 1.0000
9.750 1.3908 0.02960 0.02054 -0.0600 0.1012 1.0000
10.000 1.3994 0.03132 0.02196 -0.0579 0.0548 1.0000
10.250 1.4053 0.03325 0.02392 -0.0552 0.0425 1.0000
10.500 1.4109 0.03501 0.02587 -0.0525 0.0372 1.0000
10.750 1.4118 0.03691 0.02790 -0.0492 0.0351 1.0000
11.000 1.4130 0.03886 0.03007 -0.0464 0.0340 1.0000
11.250 1.4122 0.04105 0.03248 -0.0438 0.0330 1.0000
11.500 1.4094 0.04353 0.03518 -0.0416 0.0321 1.0000
11.750 1.4046 0.04635 0.03822 -0.0398 0.0313 1.0000
12.000 1.3978 0.04959 0.04166 -0.0386 0.0306 1.0000
12.250 1.3891 0.05331 0.04558 -0.0380 0.0301 1.0000
12.500 1.3786 0.05756 0.05004 -0.0381 0.0296 1.0000
12.750 1.3668 0.06233 0.05499 -0.0389 0.0293 1.0000
13.000 1.3547 0.06742 0.06028 -0.0401 0.0292 1.0000
13.250 1.3424 0.07279 0.06583 -0.0417 0.0291 1.0000
13.500 1.3303 0.07829 0.07150 -0.0434 0.0290 1.0000
13.750 1.3199 0.08357 0.07693 -0.0450 0.0290 1.0000
14.000 1.3116 0.08844 0.08194 -0.0462 0.0291 1.0000
14.250 1.3067 0.09268 0.08631 -0.0469 0.0291 1.0000
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Polar data table (+)
Polar graphs
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