GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Reynolds number: 500,000 Max Cl/Cd: 92.95 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe279-il-500000-n5.txt Download as CSV file: xf-goe279-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3230 0.10569 0.10338 -0.0285 1.0000 0.0105
-9.000 -0.3218 0.10301 0.10073 -0.0286 1.0000 0.0105
-8.750 -0.3227 0.10057 0.09833 -0.0282 1.0000 0.0105
-8.500 -0.3156 0.09721 0.09499 -0.0304 0.9980 0.0105
-8.250 -0.3011 0.09311 0.09089 -0.0348 0.9947 0.0105
-8.000 -0.2866 0.08907 0.08686 -0.0390 0.9897 0.0105
-7.500 -0.2565 0.08193 0.07972 -0.0459 0.9790 0.0096
-7.250 -0.2346 0.07639 0.07417 -0.0552 0.9708 0.0105
-7.000 -0.2151 0.07258 0.07034 -0.0597 0.9656 0.0104
-6.750 -0.1974 0.06910 0.06684 -0.0637 0.9575 0.0100
-6.500 -0.1752 0.06491 0.06261 -0.0695 0.9510 0.0096
-6.250 -0.1532 0.06059 0.05824 -0.0748 0.9420 0.0093
-6.000 -0.1284 0.05606 0.05364 -0.0804 0.9346 0.0091
-5.750 -0.1026 0.05160 0.04909 -0.0854 0.9269 0.0091
-5.500 -0.0747 0.04711 0.04447 -0.0902 0.9204 0.0093
-5.250 -0.0461 0.04251 0.03971 -0.0944 0.9124 0.0096
-5.000 -0.0122 0.03549 0.03237 -0.0995 0.9050 0.0106
-4.750 0.0143 0.03307 0.02979 -0.1009 0.8962 0.0110
-4.500 0.0417 0.03056 0.02711 -0.1021 0.8877 0.0114
-4.250 0.0706 0.02747 0.02377 -0.1032 0.8797 0.0120
-4.000 0.1039 0.02058 0.01620 -0.1047 0.8732 0.0141
-3.750 0.1306 0.02018 0.01571 -0.1048 0.8650 0.0147
-3.250 0.1889 0.01475 0.00942 -0.1051 0.8497 0.0185
-3.000 0.2161 0.01479 0.00942 -0.1050 0.8400 0.0193
-2.750 0.2439 0.01407 0.00852 -0.1049 0.8302 0.0207
-2.500 0.2723 0.01276 0.00685 -0.1046 0.8192 0.0233
-2.250 0.2999 0.01212 0.00607 -0.1046 0.8066 0.0245
-2.000 0.3275 0.01180 0.00566 -0.1045 0.7940 0.0254
-1.750 0.3551 0.01147 0.00524 -0.1043 0.7809 0.0267
-1.500 0.3827 0.01115 0.00479 -0.1041 0.7648 0.0283
-1.250 0.4098 0.01077 0.00425 -0.1038 0.7420 0.0293
-1.000 0.4362 0.01052 0.00381 -0.1034 0.7052 0.0300
-0.750 0.4618 0.01057 0.00361 -0.1027 0.6622 0.0308
-0.500 0.4873 0.01024 0.00306 -0.1023 0.6269 0.0318
-0.250 0.5133 0.01010 0.00277 -0.1019 0.5976 0.0327
0.000 0.5398 0.01005 0.00260 -0.1017 0.5726 0.0335
0.250 0.5668 0.01001 0.00247 -0.1015 0.5520 0.0343
0.500 0.5939 0.00997 0.00236 -0.1014 0.5339 0.0351
0.750 0.6210 0.00998 0.00229 -0.1013 0.5152 0.0362
1.000 0.6479 0.01002 0.00225 -0.1011 0.4922 0.0376
1.250 0.6744 0.01011 0.00221 -0.1009 0.4634 0.0385
1.500 0.7003 0.01028 0.00221 -0.1006 0.4268 0.0395
1.750 0.7260 0.01050 0.00226 -0.1003 0.3914 0.0406
2.000 0.7523 0.01066 0.00229 -0.1000 0.3678 0.0426
2.250 0.7785 0.01085 0.00237 -0.0998 0.3459 0.0461
2.500 0.8047 0.01105 0.00247 -0.0996 0.3261 0.0508
2.750 0.8311 0.01002 0.00280 -0.1002 0.3098 0.7229
3.250 0.8775 0.00984 0.00301 -0.0980 0.2883 1.0000
3.500 0.9043 0.01002 0.00314 -0.0978 0.2793 1.0000
3.750 0.9308 0.01023 0.00330 -0.0976 0.2697 1.0000
4.000 0.9571 0.01046 0.00346 -0.0974 0.2586 1.0000
4.250 0.9836 0.01065 0.00362 -0.0972 0.2488 1.0000
4.500 1.0098 0.01087 0.00381 -0.0970 0.2389 1.0000
4.750 1.0355 0.01114 0.00401 -0.0967 0.2237 1.0000
5.000 1.0606 0.01147 0.00423 -0.0964 0.2038 1.0000
5.250 1.0854 0.01183 0.00450 -0.0960 0.1831 1.0000
5.500 1.1092 0.01230 0.00483 -0.0955 0.1565 1.0000
5.750 1.1331 0.01275 0.00517 -0.0950 0.1375 1.0000
6.000 1.1575 0.01313 0.00551 -0.0945 0.1270 1.0000
6.250 1.1819 0.01350 0.00585 -0.0941 0.1191 1.0000
6.500 1.2066 0.01382 0.00618 -0.0937 0.1132 1.0000
6.750 1.2309 0.01416 0.00653 -0.0932 0.1070 1.0000
7.000 1.2548 0.01454 0.00691 -0.0927 0.0992 1.0000
7.250 1.2782 0.01497 0.00730 -0.0921 0.0875 1.0000
7.500 1.2965 0.01593 0.00800 -0.0908 0.0482 1.0000
7.750 1.3189 0.01643 0.00851 -0.0901 0.0432 1.0000
8.000 1.3414 0.01688 0.00902 -0.0893 0.0411 1.0000
8.250 1.3636 0.01735 0.00954 -0.0885 0.0395 1.0000
8.500 1.3854 0.01784 0.01008 -0.0877 0.0382 1.0000
8.750 1.4064 0.01838 0.01068 -0.0868 0.0366 1.0000
9.000 1.4270 0.01892 0.01131 -0.0858 0.0346 1.0000
9.250 1.4480 0.01939 0.01185 -0.0849 0.0332 1.0000
9.500 1.4680 0.01991 0.01246 -0.0838 0.0319 1.0000
9.750 1.4870 0.02050 0.01312 -0.0826 0.0305 1.0000
10.000 1.5046 0.02117 0.01384 -0.0812 0.0289 1.0000
10.250 1.5201 0.02195 0.01471 -0.0795 0.0271 1.0000
10.500 1.5342 0.02269 0.01553 -0.0776 0.0256 1.0000
10.750 1.5515 0.02312 0.01605 -0.0761 0.0245 1.0000
11.000 1.5674 0.02366 0.01667 -0.0744 0.0227 1.0000
11.250 1.5818 0.02431 0.01737 -0.0727 0.0199 1.0000
11.500 1.5942 0.02511 0.01821 -0.0707 0.0169 1.0000
11.750 1.6047 0.02607 0.01914 -0.0686 0.0134 1.0000
12.000 1.6132 0.02719 0.02032 -0.0664 0.0113 1.0000
12.250 1.6201 0.02846 0.02166 -0.0641 0.0098 1.0000
12.500 1.6267 0.02979 0.02310 -0.0619 0.0089 1.0000
12.750 1.6316 0.03132 0.02473 -0.0597 0.0082 1.0000
13.000 1.6340 0.03311 0.02662 -0.0576 0.0076 1.0000
13.250 1.6370 0.03493 0.02857 -0.0557 0.0071 1.0000
13.500 1.6395 0.03688 0.03065 -0.0540 0.0067 1.0000
13.750 1.6405 0.03905 0.03295 -0.0525 0.0064 1.0000
14.000 1.6397 0.04153 0.03556 -0.0512 0.0060 1.0000
14.250 1.6366 0.04436 0.03853 -0.0501 0.0057 1.0000
14.500 1.6311 0.04767 0.04198 -0.0494 0.0055 1.0000
14.750 1.6231 0.05151 0.04596 -0.0492 0.0053 1.0000
15.000 1.6173 0.05531 0.04992 -0.0494 0.0052 1.0000
15.250 1.6096 0.05964 0.05440 -0.0500 0.0050 1.0000
15.500 1.5999 0.06448 0.05941 -0.0512 0.0049 1.0000
15.750 1.5881 0.06981 0.06490 -0.0526 0.0049 1.0000
16.000 1.5746 0.07561 0.07085 -0.0545 0.0048 1.0000
16.250 1.5592 0.08187 0.07727 -0.0566 0.0047 1.0000
16.500 1.5420 0.08856 0.08412 -0.0591 0.0047 1.0000
16.750 1.5240 0.09555 0.09126 -0.0618 0.0047 1.0000
17.000 1.5057 0.10272 0.09858 -0.0646 0.0046 1.0000
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