GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Reynolds number: 500,000 Max Cl/Cd: 101.13 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe281-il-500000.txt Download as CSV file: xf-goe281-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3502 0.09435 0.09226 -0.0279 1.0000 0.0160
-7.750 -0.3555 0.09209 0.09005 -0.0276 1.0000 0.0160
-7.500 -0.3582 0.08845 0.08645 -0.0241 1.0000 0.0162
-7.250 -0.3579 0.08600 0.08402 -0.0226 0.9997 0.0164
-7.000 -0.3359 0.08178 0.07979 -0.0277 0.9971 0.0167
-6.750 -0.3099 0.07732 0.07531 -0.0345 0.9944 0.0171
-6.500 -0.2834 0.07282 0.07078 -0.0415 0.9904 0.0177
-6.250 -0.2521 0.06792 0.06583 -0.0498 0.9868 0.0189
-6.000 -0.1946 0.06080 0.05855 -0.0668 0.9838 0.0203
-5.750 -0.1549 0.05510 0.05269 -0.0752 0.9796 0.0205
-5.500 -0.1291 0.04857 0.04606 -0.0806 0.9751 0.0209
-5.250 -0.1029 0.04549 0.04296 -0.0835 0.9715 0.0213
-5.000 -0.0768 0.04261 0.04000 -0.0860 0.9652 0.0220
-4.750 -0.0477 0.03945 0.03671 -0.0887 0.9586 0.0232
-4.500 -0.0094 0.03625 0.03316 -0.0910 0.9506 0.0261
-4.250 0.0206 0.03359 0.03013 -0.0918 0.9422 0.0264
-4.000 0.0405 0.02823 0.02458 -0.0927 0.9312 0.0271
-3.750 0.0628 0.02632 0.02259 -0.0927 0.9204 0.0278
-3.500 0.0869 0.02465 0.02080 -0.0926 0.9090 0.0287
-3.250 0.1126 0.02300 0.01894 -0.0925 0.8965 0.0303
-3.000 0.1429 0.02313 0.01869 -0.0913 0.8826 0.0339
-2.750 0.1686 0.01937 0.01453 -0.0916 0.8676 0.0353
-2.500 0.1939 0.01797 0.01304 -0.0916 0.8507 0.0366
-2.250 0.2205 0.01699 0.01189 -0.0914 0.8340 0.0386
-2.000 0.2483 0.01637 0.01102 -0.0911 0.8179 0.0419
-1.250 0.3308 0.01399 0.00793 -0.0908 0.7682 0.0587
-1.000 0.3578 0.01321 0.00713 -0.0909 0.7511 0.0637
-0.750 0.3852 0.01267 0.00648 -0.0909 0.7353 0.0764
-0.500 0.4125 0.01222 0.00595 -0.0911 0.7208 0.0930
0.000 0.4706 0.01132 0.00462 -0.0900 0.6922 0.0714
0.250 0.4989 0.01058 0.00379 -0.0895 0.6787 0.0533
0.500 0.5269 0.01026 0.00333 -0.0892 0.6657 0.0456
0.750 0.5548 0.01020 0.00324 -0.0891 0.6535 0.0440
1.000 0.5826 0.00979 0.00281 -0.0890 0.6419 0.0429
1.250 0.6105 0.00962 0.00259 -0.0890 0.6288 0.0427
1.500 0.6382 0.00952 0.00244 -0.0889 0.6144 0.0432
1.750 0.6659 0.00948 0.00234 -0.0888 0.5987 0.0437
2.000 0.6936 0.00946 0.00227 -0.0888 0.5822 0.0444
2.250 0.7211 0.00947 0.00219 -0.0887 0.5639 0.0472
2.500 0.7487 0.00952 0.00218 -0.0887 0.5417 0.0487
2.750 0.7756 0.00964 0.00219 -0.0885 0.5125 0.0517
3.000 0.7974 0.00795 0.00241 -0.0878 0.4817 1.0000
3.250 0.8237 0.00824 0.00252 -0.0875 0.4571 1.0000
3.500 0.8503 0.00850 0.00267 -0.0874 0.4400 1.0000
3.750 0.8770 0.00873 0.00282 -0.0872 0.4260 1.0000
4.000 0.9038 0.00896 0.00299 -0.0871 0.4136 1.0000
4.250 0.9304 0.00920 0.00316 -0.0870 0.3995 1.0000
4.500 0.9565 0.00948 0.00336 -0.0868 0.3775 1.0000
4.750 0.9828 0.00972 0.00353 -0.0867 0.3552 1.0000
5.000 1.0088 0.01000 0.00372 -0.0865 0.3315 1.0000
5.250 1.0339 0.01040 0.00394 -0.0862 0.2937 1.0000
5.500 1.0577 0.01094 0.00428 -0.0857 0.2550 1.0000
5.750 1.0813 0.01150 0.00465 -0.0852 0.2228 1.0000
6.000 1.1052 0.01201 0.00502 -0.0848 0.1946 1.0000
6.250 1.1267 0.01282 0.00549 -0.0841 0.1399 1.0000
6.500 1.1463 0.01383 0.00617 -0.0831 0.0903 1.0000
6.750 1.1622 0.01530 0.00725 -0.0814 0.0231 1.0000
7.000 1.1852 0.01586 0.00787 -0.0807 0.0201 1.0000
7.250 1.2077 0.01648 0.00862 -0.0798 0.0179 1.0000
7.500 1.2300 0.01707 0.00930 -0.0790 0.0169 1.0000
7.750 1.2513 0.01776 0.01010 -0.0780 0.0161 1.0000
8.000 1.2713 0.01855 0.01099 -0.0768 0.0153 1.0000
8.250 1.2898 0.01944 0.01198 -0.0754 0.0147 1.0000
8.500 1.3063 0.02046 0.01309 -0.0738 0.0141 1.0000
8.750 1.3202 0.02163 0.01436 -0.0717 0.0137 1.0000
9.000 1.3301 0.02306 0.01590 -0.0692 0.0132 1.0000
9.250 1.3317 0.02502 0.01796 -0.0655 0.0126 1.0000
9.500 1.3323 0.02685 0.01987 -0.0615 0.0123 1.0000
9.750 1.3433 0.02782 0.02093 -0.0592 0.0120 1.0000
10.000 1.3516 0.02913 0.02232 -0.0567 0.0119 1.0000
10.250 1.3595 0.03058 0.02386 -0.0543 0.0117 1.0000
10.500 1.3675 0.03216 0.02553 -0.0520 0.0116 1.0000
10.750 1.3758 0.03385 0.02732 -0.0499 0.0114 1.0000
11.000 1.3846 0.03567 0.02924 -0.0479 0.0113 1.0000
11.250 1.3946 0.03770 0.03137 -0.0460 0.0114 1.0000
11.500 1.4071 0.04008 0.03386 -0.0444 0.0115 1.0000
14.500 1.3575 0.08242 0.07864 -0.0336 0.0149 1.0000
14.750 1.3415 0.08795 0.08434 -0.0356 0.0148 1.0000
15.000 1.3247 0.09401 0.09056 -0.0382 0.0148 1.0000
15.250 1.3075 0.10051 0.09722 -0.0413 0.0148 1.0000
15.500 1.2899 0.10756 0.10443 -0.0452 0.0147 1.0000
15.750 1.2719 0.11524 0.11227 -0.0498 0.0148 1.0000
16.000 1.2534 0.12346 0.12065 -0.0549 0.0148 1.0000
16.250 1.2345 0.13226 0.12960 -0.0607 0.0149 1.0000
16.500 1.2152 0.14179 0.13928 -0.0671 0.0151 1.0000
16.750 1.1947 0.15237 0.14999 -0.0743 0.0154 1.0000
17.000 1.1730 0.16410 0.16185 -0.0822 0.0158 1.0000
17.250 1.1499 0.17704 0.17488 -0.0907 0.0164 1.0000
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Polar data table (+)
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