GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.23 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe281-il-1000000.txt Download as CSV file: xf-goe281-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 281 (DAIMLER XII) 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3861 0.12231 0.12067 -0.0142 1.0000 0.0092
-10.250 -0.3804 0.11878 0.11715 -0.0158 1.0000 0.0093
-10.000 -0.3765 0.11445 0.11283 -0.0166 1.0000 0.0094
-9.750 -0.3698 0.11141 0.10979 -0.0174 1.0000 0.0095
-9.500 -0.3628 0.10851 0.10690 -0.0186 1.0000 0.0097
-9.250 -0.3558 0.10562 0.10403 -0.0198 1.0000 0.0099
-9.000 -0.3490 0.10269 0.10111 -0.0212 1.0000 0.0102
-8.750 -0.3424 0.09970 0.09813 -0.0226 1.0000 0.0107
-8.500 -0.3364 0.09657 0.09501 -0.0241 1.0000 0.0115
-8.000 -0.2341 0.07408 0.07265 -0.0401 0.9944 0.0123
-7.750 -0.2293 0.06869 0.06727 -0.0422 0.9906 0.0125
-7.500 -0.2182 0.06512 0.06370 -0.0440 0.9861 0.0127
-7.250 -0.2089 0.06173 0.06031 -0.0463 0.9793 0.0129
-7.000 -0.2014 0.05817 0.05674 -0.0490 0.9703 0.0132
-6.750 -0.1939 0.05458 0.05314 -0.0518 0.9601 0.0135
-6.500 -0.1841 0.05084 0.04937 -0.0549 0.9507 0.0141
-5.250 -0.1024 0.03976 0.03761 -0.0836 0.9305 0.0163
-5.000 -0.0828 0.03823 0.03604 -0.0839 0.9205 0.0166
-4.750 -0.0603 0.03639 0.03411 -0.0846 0.9092 0.0172
-4.500 -0.0349 0.03404 0.03160 -0.0857 0.8960 0.0184
-4.250 0.0007 0.03081 0.02803 -0.0864 0.8821 0.0203
-4.000 0.0282 0.02774 0.02465 -0.0869 0.8661 0.0204
-3.750 0.0526 0.02220 0.01867 -0.0880 0.8496 0.0211
-3.500 0.0777 0.02098 0.01731 -0.0882 0.8311 0.0215
-3.250 0.1037 0.01993 0.01609 -0.0884 0.8131 0.0221
-3.000 0.1307 0.01882 0.01478 -0.0885 0.7953 0.0231
-2.750 0.1606 0.01884 0.01455 -0.0880 0.7776 0.0261
-2.500 0.1891 0.01801 0.01342 -0.0878 0.7585 0.0263
-2.250 0.2171 0.01691 0.01204 -0.0878 0.7388 0.0264
-2.000 0.2448 0.01375 0.00848 -0.0882 0.7206 0.0273
-1.750 0.2725 0.01291 0.00754 -0.0884 0.7038 0.0280
-1.500 0.3003 0.01234 0.00687 -0.0886 0.6883 0.0289
-1.250 0.3284 0.01189 0.00630 -0.0886 0.6745 0.0304
-1.000 0.3568 0.01162 0.00590 -0.0886 0.6626 0.0324
-0.750 0.3853 0.01216 0.00632 -0.0885 0.6507 0.0340
-0.500 0.4134 0.01036 0.00439 -0.0888 0.6404 0.0370
-0.250 0.4415 0.01002 0.00403 -0.0889 0.6303 0.0392
1.000 0.5829 0.00879 0.00250 -0.0888 0.5695 0.0348
1.250 0.6110 0.00847 0.00213 -0.0889 0.5519 0.0324
1.500 0.6388 0.00840 0.00196 -0.0889 0.5238 0.0327
1.750 0.6660 0.00849 0.00188 -0.0888 0.4847 0.0334
2.000 0.6931 0.00863 0.00188 -0.0888 0.4548 0.0339
2.250 0.7206 0.00873 0.00189 -0.0888 0.4366 0.0342
2.500 0.7482 0.00879 0.00188 -0.0888 0.4217 0.0347
2.750 0.7759 0.00885 0.00189 -0.0889 0.4099 0.0361
3.000 0.8037 0.00892 0.00193 -0.0889 0.3999 0.0369
3.250 0.8313 0.00903 0.00199 -0.0889 0.3898 0.0381
3.500 0.8591 0.00910 0.00206 -0.0890 0.3800 0.0430
3.750 0.8820 0.00746 0.00235 -0.0886 0.3660 1.0000
4.000 0.9089 0.00770 0.00246 -0.0885 0.3414 1.0000
4.250 0.9357 0.00795 0.00259 -0.0884 0.3162 1.0000
4.500 0.9612 0.00837 0.00280 -0.0882 0.2754 1.0000
4.750 0.9864 0.00882 0.00306 -0.0880 0.2398 1.0000
5.000 1.0121 0.00919 0.00330 -0.0878 0.2176 1.0000
5.250 1.0381 0.00950 0.00353 -0.0876 0.1986 1.0000
5.500 1.0626 0.01000 0.00383 -0.0873 0.1631 1.0000
5.750 1.0845 0.01085 0.00433 -0.0866 0.1084 1.0000
6.000 1.1017 0.01231 0.00528 -0.0852 0.0217 1.0000
6.250 1.1271 0.01266 0.00566 -0.0848 0.0167 1.0000
6.500 1.1520 0.01303 0.00609 -0.0844 0.0152 1.0000
6.750 1.1761 0.01352 0.00663 -0.0839 0.0133 1.0000
7.000 1.1995 0.01407 0.00726 -0.0832 0.0122 1.0000
7.250 1.2235 0.01450 0.00773 -0.0827 0.0117 1.0000
7.500 1.2469 0.01500 0.00830 -0.0820 0.0111 1.0000
7.750 1.2696 0.01555 0.00890 -0.0813 0.0105 1.0000
8.000 1.2916 0.01616 0.00956 -0.0805 0.0099 1.0000
8.250 1.3123 0.01686 0.01031 -0.0795 0.0094 1.0000
8.500 1.3246 0.01840 0.01200 -0.0772 0.0086 1.0000
8.750 1.3443 0.01908 0.01275 -0.0760 0.0083 1.0000
9.000 1.3635 0.01977 0.01350 -0.0748 0.0080 1.0000
9.250 1.3805 0.02060 0.01440 -0.0732 0.0078 1.0000
9.500 1.3957 0.02153 0.01540 -0.0714 0.0075 1.0000
9.750 1.4091 0.02252 0.01646 -0.0694 0.0073 1.0000
10.000 1.4203 0.02355 0.01755 -0.0670 0.0071 1.0000
10.250 1.4278 0.02458 0.01867 -0.0641 0.0069 1.0000
10.500 1.4347 0.02569 0.01985 -0.0612 0.0067 1.0000
10.750 1.4417 0.02687 0.02110 -0.0586 0.0065 1.0000
11.000 1.4479 0.02818 0.02248 -0.0561 0.0063 1.0000
11.250 1.4521 0.02972 0.02409 -0.0536 0.0062 1.0000
11.500 1.4536 0.03161 0.02605 -0.0512 0.0060 1.0000
11.750 1.4507 0.03415 0.02866 -0.0485 0.0059 1.0000
12.000 1.4458 0.03762 0.03223 -0.0454 0.0056 1.0000
12.250 1.4514 0.03910 0.03385 -0.0442 0.0055 1.0000
12.500 1.4559 0.04101 0.03587 -0.0431 0.0054 1.0000
12.750 1.4588 0.04325 0.03823 -0.0419 0.0053 1.0000
13.000 1.4599 0.04583 0.04094 -0.0407 0.0052 1.0000
13.250 1.4599 0.04863 0.04386 -0.0396 0.0052 1.0000
13.500 1.4590 0.05161 0.04697 -0.0387 0.0051 1.0000
13.750 1.4563 0.05486 0.05037 -0.0379 0.0051 1.0000
14.000 1.4520 0.05839 0.05404 -0.0374 0.0050 1.0000
14.250 1.4458 0.06228 0.05808 -0.0372 0.0050 1.0000
14.500 1.4378 0.06642 0.06238 -0.0373 0.0050 1.0000
14.750 1.4284 0.07091 0.06703 -0.0379 0.0050 1.0000
15.000 1.4169 0.07591 0.07219 -0.0388 0.0050 1.0000
15.250 1.4047 0.08114 0.07758 -0.0401 0.0050 1.0000
15.500 1.3916 0.08677 0.08337 -0.0420 0.0050 1.0000
15.750 1.3771 0.09293 0.08968 -0.0444 0.0050 1.0000
16.000 1.3620 0.09942 0.09633 -0.0472 0.0050 1.0000
16.250 1.3471 0.10617 0.10323 -0.0505 0.0050 1.0000
16.500 1.3321 0.11325 0.11046 -0.0541 0.0050 1.0000
16.750 1.3160 0.12079 0.11814 -0.0582 0.0050 1.0000
17.000 1.3003 0.12849 0.12598 -0.0626 0.0050 1.0000
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Polar data table (+)
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