GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.89 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe279-il-1000000.txt Download as CSV file: xf-goe279-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 279 (DAIMLER X) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2643 0.09586 0.09433 -0.0283 1.0000 0.0107
-9.250 -0.2663 0.09310 0.09160 -0.0275 1.0000 0.0112
-9.000 -0.2685 0.08983 0.08834 -0.0281 0.9996 0.0116
-8.750 -0.2622 0.08540 0.08391 -0.0314 0.9983 0.0117
-8.500 -0.2552 0.08096 0.07948 -0.0348 0.9968 0.0117
-8.250 -0.2466 0.07656 0.07507 -0.0381 0.9952 0.0117
-8.000 -0.2398 0.07146 0.06998 -0.0406 0.9934 0.0118
-7.750 -0.2283 0.06786 0.06638 -0.0423 0.9908 0.0120
-7.500 -0.2166 0.06413 0.06265 -0.0453 0.9879 0.0122
-7.250 -0.2041 0.06015 0.05867 -0.0493 0.9842 0.0124
-7.000 -0.1932 0.05618 0.05471 -0.0534 0.9759 0.0126
-6.750 -0.1793 0.05190 0.05041 -0.0582 0.9688 0.0129
-6.500 -0.1665 0.04777 0.04624 -0.0623 0.9588 0.0133
-6.250 -0.1524 0.04351 0.04194 -0.0663 0.9483 0.0140
-6.000 -0.1279 0.03713 0.03542 -0.0750 0.9393 0.0147
-5.750 -0.1082 0.03247 0.03066 -0.0784 0.9307 0.0148
-5.500 -0.0941 0.02772 0.02582 -0.0805 0.9217 0.0151
-5.250 -0.0751 0.02525 0.02327 -0.0815 0.9138 0.0154
-5.000 -0.0534 0.02276 0.02071 -0.0829 0.9061 0.0159
-4.750 -0.0300 0.02006 0.01788 -0.0844 0.8992 0.0167
-4.500 0.0035 0.01619 0.01372 -0.0868 0.8930 0.0184
-4.250 0.0286 0.01295 0.01025 -0.0877 0.8864 0.0184
-4.000 0.0500 0.00978 0.00688 -0.0889 0.8799 0.0190
-3.750 0.0740 0.00885 0.00586 -0.0891 0.8718 0.0196
-3.500 0.0997 0.00778 0.00465 -0.0894 0.8640 0.0209
-3.250 0.1306 0.00632 0.00280 -0.0890 0.8571 0.0227
-3.000 0.1608 0.01692 0.01296 -0.0938 0.8661 0.0217
-2.750 0.1904 0.01378 0.00935 -0.0935 0.8584 0.0222
-2.500 0.2183 0.01246 0.00779 -0.0935 0.8514 0.0239
-2.250 0.2454 0.01290 0.00830 -0.0936 0.8423 0.0255
-2.000 0.2740 0.01179 0.00697 -0.0934 0.8335 0.0267
-1.500 0.3305 0.00996 0.00476 -0.0931 0.8136 0.0295
-1.250 0.3581 0.00982 0.00462 -0.0931 0.8014 0.0310
-1.000 0.3858 0.00923 0.00391 -0.0929 0.7829 0.0313
-0.750 0.4131 0.00886 0.00341 -0.0926 0.7579 0.0321
-0.500 0.4399 0.00869 0.00310 -0.0922 0.7212 0.0335
-0.250 0.4655 0.00865 0.00280 -0.0917 0.6656 0.0342
0.000 0.4917 0.00863 0.00257 -0.0913 0.6245 0.0347
0.250 0.5185 0.00859 0.00241 -0.0910 0.5958 0.0351
0.500 0.5457 0.00857 0.00228 -0.0909 0.5715 0.0357
0.750 0.5731 0.00824 0.00187 -0.0909 0.5486 0.0376
1.000 0.6005 0.00823 0.00177 -0.0908 0.5250 0.0388
1.250 0.6280 0.00826 0.00171 -0.0907 0.5020 0.0400
1.500 0.6552 0.00833 0.00168 -0.0906 0.4757 0.0413
1.750 0.6821 0.00846 0.00168 -0.0904 0.4438 0.0430
2.000 0.7086 0.00866 0.00174 -0.0902 0.4073 0.0447
2.250 0.7352 0.00882 0.00174 -0.0901 0.3757 0.0492
2.500 0.7618 0.00901 0.00181 -0.0899 0.3494 0.0546
2.750 0.7823 0.00733 0.00210 -0.0889 0.3302 1.0000
3.000 0.8093 0.00754 0.00219 -0.0888 0.3151 1.0000
3.250 0.8366 0.00771 0.00229 -0.0887 0.3035 1.0000
3.500 0.8639 0.00787 0.00240 -0.0886 0.2941 1.0000
3.750 0.8910 0.00805 0.00253 -0.0885 0.2844 1.0000
4.000 0.9183 0.00819 0.00264 -0.0885 0.2755 1.0000
4.250 0.9453 0.00838 0.00277 -0.0884 0.2657 1.0000
4.500 0.9721 0.00857 0.00291 -0.0882 0.2540 1.0000
4.750 0.9988 0.00877 0.00307 -0.0881 0.2411 1.0000
5.000 1.0251 0.00902 0.00323 -0.0879 0.2251 1.0000
5.250 1.0509 0.00932 0.00343 -0.0877 0.2020 1.0000
5.500 1.0753 0.00979 0.00372 -0.0872 0.1679 1.0000
5.750 1.0993 0.01031 0.00406 -0.0867 0.1375 1.0000
6.000 1.1243 0.01068 0.00436 -0.0864 0.1233 1.0000
6.250 1.1495 0.01102 0.00464 -0.0861 0.1130 1.0000
6.500 1.1745 0.01138 0.00496 -0.0857 0.1019 1.0000
6.750 1.1985 0.01184 0.00530 -0.0852 0.0784 1.0000
7.000 1.2190 0.01275 0.00596 -0.0842 0.0422 1.0000
7.250 1.2431 0.01319 0.00639 -0.0836 0.0379 1.0000
7.500 1.2674 0.01358 0.00682 -0.0831 0.0360 1.0000
7.750 1.2920 0.01392 0.00720 -0.0827 0.0352 1.0000
8.000 1.3161 0.01429 0.00762 -0.0822 0.0340 1.0000
8.250 1.3396 0.01471 0.00810 -0.0816 0.0327 1.0000
8.500 1.3624 0.01520 0.00862 -0.0809 0.0313 1.0000
8.750 1.3842 0.01579 0.00926 -0.0800 0.0295 1.0000
9.000 1.4040 0.01657 0.01014 -0.0789 0.0278 1.0000
9.250 1.4274 0.01690 0.01051 -0.0783 0.0273 1.0000
9.500 1.4501 0.01728 0.01093 -0.0777 0.0265 1.0000
9.750 1.4723 0.01769 0.01139 -0.0770 0.0254 1.0000
10.000 1.4939 0.01814 0.01186 -0.0762 0.0241 1.0000
10.250 1.5136 0.01874 0.01250 -0.0751 0.0227 1.0000
10.500 1.5288 0.01971 0.01356 -0.0733 0.0211 1.0000
10.750 1.5520 0.01991 0.01379 -0.0728 0.0204 1.0000
11.000 1.5737 0.02022 0.01412 -0.0721 0.0191 1.0000
11.250 1.5943 0.02060 0.01450 -0.0712 0.0177 1.0000
11.500 1.6093 0.02140 0.01533 -0.0695 0.0161 1.0000
11.750 1.6279 0.02183 0.01581 -0.0683 0.0151 1.0000
12.000 1.6433 0.02236 0.01636 -0.0665 0.0140 1.0000
12.250 1.6537 0.02318 0.01721 -0.0640 0.0128 1.0000
12.500 1.6630 0.02410 0.01821 -0.0615 0.0120 1.0000
12.750 1.6742 0.02492 0.01911 -0.0594 0.0113 1.0000
13.000 1.6841 0.02585 0.02010 -0.0573 0.0107 1.0000
13.250 1.6913 0.02702 0.02132 -0.0550 0.0100 1.0000
13.500 1.6895 0.02891 0.02332 -0.0519 0.0093 1.0000
13.750 1.6977 0.03010 0.02461 -0.0501 0.0090 1.0000
14.000 1.7033 0.03158 0.02620 -0.0482 0.0087 1.0000
14.250 1.7070 0.03328 0.02799 -0.0465 0.0084 1.0000
14.500 1.7094 0.03519 0.03001 -0.0449 0.0081 1.0000
14.750 1.7101 0.03736 0.03228 -0.0435 0.0078 1.0000
15.000 1.7079 0.03994 0.03497 -0.0422 0.0076 1.0000
15.250 1.7021 0.04310 0.03825 -0.0413 0.0073 1.0000
15.500 1.6913 0.04708 0.04236 -0.0409 0.0071 1.0000
15.750 1.6760 0.05206 0.04750 -0.0413 0.0070 1.0000
16.000 1.6581 0.05785 0.05346 -0.0425 0.0069 1.0000
16.250 1.6463 0.06307 0.05883 -0.0440 0.0068 1.0000
16.500 1.6345 0.06849 0.06439 -0.0458 0.0067 1.0000
16.750 1.6193 0.07457 0.07061 -0.0479 0.0067 1.0000
17.000 1.6008 0.08133 0.07751 -0.0504 0.0067 1.0000
17.250 1.5823 0.08825 0.08458 -0.0531 0.0066 1.0000
17.500 1.5608 0.09575 0.09222 -0.0560 0.0066 1.0000
17.750 1.5403 0.10320 0.09979 -0.0591 0.0066 1.0000
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