GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Reynolds number: 200,000 Max Cl/Cd: 75.23 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe281-il-200000-n5.txt Download as CSV file: xf-goe281-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3308 0.09716 0.09389 -0.0293 1.0000 0.0203
-7.750 -0.3373 0.09509 0.09189 -0.0286 1.0000 0.0203
-7.500 -0.3400 0.09258 0.08943 -0.0288 1.0000 0.0203
-7.250 -0.3328 0.08902 0.08590 -0.0316 0.9981 0.0203
-7.000 -0.3088 0.08378 0.08062 -0.0389 0.9933 0.0204
-6.750 -0.2833 0.07845 0.07526 -0.0462 0.9881 0.0204
-6.500 -0.2562 0.07306 0.06981 -0.0533 0.9833 0.0204
-6.250 -0.2398 0.06863 0.06539 -0.0552 0.9790 0.0209
-6.000 -0.2179 0.06616 0.06290 -0.0569 0.9761 0.0234
-5.750 -0.1690 0.06048 0.05700 -0.0703 0.9679 0.0265
-5.500 -0.1334 0.05518 0.05151 -0.0772 0.9621 0.0267
-5.250 -0.1010 0.05022 0.04633 -0.0822 0.9544 0.0267
-4.750 -0.0559 0.04299 0.03902 -0.0867 0.9389 0.0294
-4.500 -0.0265 0.03977 0.03560 -0.0892 0.9296 0.0316
-4.250 0.0183 0.03721 0.03235 -0.0924 0.9221 0.0355
-4.000 0.0392 0.01582 0.01140 -0.0890 0.8795 0.0387
-3.750 0.0720 0.01513 0.01014 -0.0894 0.8667 0.0464
-3.500 0.0929 0.01155 0.00645 -0.0907 0.8564 0.0485
-3.250 0.1170 0.01010 0.00488 -0.0910 0.8448 0.0511
-2.750 0.1813 0.02206 0.01574 -0.0964 0.8534 0.0433
-2.500 0.2105 0.02005 0.01334 -0.0962 0.8398 0.0397
-2.250 0.2392 0.01866 0.01159 -0.0959 0.8251 0.0388
-2.000 0.2668 0.01782 0.01052 -0.0958 0.8104 0.0408
-1.750 0.2952 0.01679 0.00920 -0.0955 0.7973 0.0395
-1.500 0.3235 0.01593 0.00804 -0.0951 0.7843 0.0382
-1.250 0.3514 0.01527 0.00716 -0.0948 0.7710 0.0376
-1.000 0.3790 0.01469 0.00642 -0.0945 0.7576 0.0375
-0.750 0.4065 0.01418 0.00579 -0.0943 0.7445 0.0376
-0.500 0.4339 0.01373 0.00524 -0.0941 0.7322 0.0380
-0.250 0.4611 0.01335 0.00480 -0.0938 0.7191 0.0386
0.000 0.4881 0.01308 0.00449 -0.0936 0.7047 0.0408
0.500 0.5420 0.01264 0.00390 -0.0931 0.6741 0.0417
0.750 0.5691 0.01250 0.00368 -0.0929 0.6593 0.0416
1.000 0.5961 0.01241 0.00351 -0.0927 0.6440 0.0417
1.250 0.6232 0.01238 0.00339 -0.0925 0.6288 0.0419
1.500 0.6502 0.01238 0.00330 -0.0923 0.6140 0.0423
1.750 0.6774 0.01240 0.00324 -0.0921 0.6000 0.0431
2.000 0.7045 0.01244 0.00322 -0.0919 0.5851 0.0441
2.250 0.7315 0.01249 0.00322 -0.0917 0.5696 0.0458
2.500 0.7585 0.01255 0.00326 -0.0916 0.5514 0.0494
2.750 0.7823 0.01144 0.00349 -0.0914 0.5301 0.6478
3.250 0.8325 0.01127 0.00357 -0.0899 0.4757 1.0000
3.500 0.8575 0.01160 0.00373 -0.0894 0.4530 1.0000
3.750 0.8829 0.01192 0.00393 -0.0890 0.4343 1.0000
4.000 0.9082 0.01225 0.00415 -0.0887 0.4175 1.0000
4.250 0.9337 0.01256 0.00440 -0.0883 0.4023 1.0000
4.500 0.9593 0.01286 0.00467 -0.0880 0.3885 1.0000
4.750 0.9849 0.01314 0.00495 -0.0878 0.3753 1.0000
5.000 1.0104 0.01343 0.00523 -0.0874 0.3607 1.0000
5.250 1.0348 0.01380 0.00554 -0.0870 0.3332 1.0000
5.500 1.0573 0.01433 0.00585 -0.0863 0.2885 1.0000
5.750 1.0788 0.01499 0.00628 -0.0855 0.2496 1.0000
6.000 1.1007 0.01563 0.00677 -0.0848 0.2211 1.0000
6.250 1.1228 0.01624 0.00729 -0.0841 0.1947 1.0000
6.500 1.1441 0.01693 0.00783 -0.0833 0.1609 1.0000
6.750 1.1623 0.01795 0.00853 -0.0822 0.1170 1.0000
7.000 1.1763 0.01943 0.00956 -0.0805 0.0470 1.0000
7.250 1.1920 0.02072 0.01072 -0.0788 0.0212 1.0000
7.500 1.2124 0.02143 0.01160 -0.0776 0.0191 1.0000
7.750 1.2314 0.02225 0.01258 -0.0763 0.0170 1.0000
8.000 1.2484 0.02326 0.01375 -0.0748 0.0149 1.0000
8.250 1.2637 0.02441 0.01512 -0.0730 0.0138 1.0000
8.500 1.2766 0.02566 0.01658 -0.0709 0.0132 1.0000
8.750 1.2900 0.02675 0.01786 -0.0689 0.0128 1.0000
9.000 1.3010 0.02790 0.01916 -0.0666 0.0123 1.0000
9.250 1.3083 0.02908 0.02048 -0.0638 0.0116 1.0000
9.500 1.3140 0.03042 0.02194 -0.0610 0.0109 1.0000
9.750 1.3175 0.03199 0.02363 -0.0583 0.0105 1.0000
10.000 1.3194 0.03379 0.02553 -0.0556 0.0102 1.0000
10.250 1.3205 0.03576 0.02761 -0.0532 0.0099 1.0000
10.500 1.3213 0.03790 0.02985 -0.0510 0.0097 1.0000
10.750 1.3218 0.04020 0.03224 -0.0492 0.0095 1.0000
11.000 1.3224 0.04265 0.03480 -0.0475 0.0093 1.0000
11.250 1.3234 0.04519 0.03742 -0.0459 0.0091 1.0000
11.500 1.3256 0.04779 0.04006 -0.0444 0.0090 1.0000
11.750 1.3310 0.05032 0.04263 -0.0427 0.0088 1.0000
12.000 1.3397 0.05292 0.04528 -0.0410 0.0086 1.0000
12.250 1.3410 0.05541 0.04799 -0.0403 0.0084 1.0000
12.500 1.3416 0.05812 0.05091 -0.0397 0.0082 1.0000
12.750 1.3414 0.06105 0.05405 -0.0393 0.0079 1.0000
13.000 1.3406 0.06420 0.05740 -0.0391 0.0076 1.0000
13.250 1.3387 0.06759 0.06098 -0.0389 0.0074 1.0000
13.500 1.3357 0.07126 0.06484 -0.0388 0.0073 1.0000
13.750 1.3310 0.07520 0.06901 -0.0391 0.0072 1.0000
14.000 1.3246 0.07945 0.07346 -0.0396 0.0072 1.0000
14.250 1.3168 0.08402 0.07822 -0.0406 0.0071 1.0000
14.500 1.3079 0.08893 0.08333 -0.0419 0.0071 1.0000
14.750 1.2979 0.09416 0.08877 -0.0437 0.0071 1.0000
15.000 1.2871 0.09977 0.09457 -0.0460 0.0070 1.0000
15.250 1.2758 0.10574 0.10074 -0.0487 0.0070 1.0000
15.500 1.2640 0.11204 0.10723 -0.0518 0.0070 1.0000
15.750 1.2518 0.11869 0.11406 -0.0554 0.0071 1.0000
16.000 1.2393 0.12566 0.12121 -0.0594 0.0071 1.0000
16.250 1.2269 0.13296 0.12868 -0.0637 0.0071 1.0000
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Polar data table (+)
Polar graphs
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