GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Reynolds number: 500,000 Max Cl/Cd: 100.89 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe277-il-500000.txt Download as CSV file: xf-goe277-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 277 (DAIMLER VIII) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3442 0.08663 0.08450 -0.0245 1.0000 0.0201
-7.500 -0.3500 0.08465 0.08257 -0.0232 1.0000 0.0204
-7.250 -0.3552 0.08253 0.08050 -0.0225 1.0000 0.0207
-7.000 -0.3613 0.08043 0.07844 -0.0217 1.0000 0.0211
-6.750 -0.3454 0.07629 0.07429 -0.0272 0.9979 0.0221
-6.500 -0.2927 0.06768 0.06554 -0.0478 0.9928 0.0237
-6.250 -0.2561 0.06122 0.05896 -0.0573 0.9884 0.0238
-5.000 -0.0912 0.03542 0.03233 -0.0844 0.9665 0.0310
-4.750 -0.0649 0.03323 0.03010 -0.0860 0.9588 0.0317
-4.500 -0.0392 0.03139 0.02817 -0.0869 0.9501 0.0328
-4.250 -0.0114 0.02924 0.02587 -0.0878 0.9418 0.0346
-4.000 0.0216 0.02880 0.02500 -0.0872 0.9301 0.0389
-3.750 0.0434 0.02311 0.01896 -0.0882 0.9182 0.0407
-3.500 0.0677 0.02174 0.01752 -0.0880 0.9047 0.0419
-3.250 0.0930 0.02056 0.01620 -0.0877 0.8898 0.0437
-3.000 0.1197 0.01958 0.01499 -0.0873 0.8733 0.0475
-2.750 0.1471 0.01782 0.01276 -0.0869 0.8549 0.0525
-2.500 0.1727 0.01667 0.01154 -0.0867 0.8324 0.0544
-2.250 -0.0448 0.09178 0.08950 -0.0324 0.9262 0.0393
-1.500 0.2824 0.01244 0.00611 -0.0844 0.7377 0.0467
-1.250 0.3100 0.01152 0.00495 -0.0840 0.7199 0.0444
-1.000 0.3375 0.01097 0.00426 -0.0837 0.7023 0.0439
-0.750 0.3649 0.01056 0.00374 -0.0834 0.6844 0.0439
-0.500 0.3922 0.01026 0.00336 -0.0832 0.6653 0.0445
-0.250 0.4194 0.01006 0.00306 -0.0829 0.6446 0.0458
0.000 0.4468 0.00983 0.00274 -0.0827 0.6214 0.0463
0.250 0.4739 0.00969 0.00249 -0.0825 0.5974 0.0474
0.500 0.5011 0.00962 0.00230 -0.0822 0.5729 0.0486
0.750 0.5283 0.00961 0.00218 -0.0821 0.5499 0.0499
1.000 0.5554 0.00959 0.00204 -0.0819 0.5281 0.0522
1.250 0.5827 0.00960 0.00197 -0.0817 0.5074 0.0581
1.500 0.6100 0.00964 0.00195 -0.0816 0.4862 0.0751
1.750 0.6323 0.00768 0.00211 -0.0809 0.4669 1.0000
2.000 0.6595 0.00787 0.00216 -0.0808 0.4465 1.0000
2.250 0.6865 0.00807 0.00224 -0.0806 0.4278 1.0000
2.500 0.7135 0.00828 0.00233 -0.0805 0.4118 1.0000
2.750 0.7405 0.00849 0.00244 -0.0803 0.3982 1.0000
3.000 0.7675 0.00870 0.00256 -0.0802 0.3859 1.0000
3.250 0.7944 0.00892 0.00269 -0.0800 0.3757 1.0000
3.500 0.8215 0.00911 0.00285 -0.0799 0.3675 1.0000
3.750 0.8485 0.00932 0.00301 -0.0798 0.3610 1.0000
4.000 0.8755 0.00950 0.00317 -0.0797 0.3541 1.0000
4.250 0.9022 0.00973 0.00334 -0.0795 0.3470 1.0000
4.500 0.9294 0.00990 0.00352 -0.0794 0.3408 1.0000
4.750 0.9559 0.01013 0.00373 -0.0793 0.3359 1.0000
5.000 0.9828 0.01033 0.00393 -0.0791 0.3313 1.0000
5.250 1.0098 0.01050 0.00414 -0.0790 0.3260 1.0000
5.500 1.0359 0.01077 0.00436 -0.0788 0.3188 1.0000
5.750 1.0629 0.01088 0.00452 -0.0787 0.3105 1.0000
6.000 1.0891 0.01111 0.00474 -0.0785 0.3029 1.0000
6.250 1.1158 0.01126 0.00493 -0.0784 0.2941 1.0000
6.500 1.1421 0.01145 0.00513 -0.0782 0.2854 1.0000
6.750 1.1681 0.01167 0.00535 -0.0780 0.2762 1.0000
7.000 1.1945 0.01184 0.00557 -0.0779 0.2648 1.0000
7.250 1.2199 0.01210 0.00579 -0.0776 0.2466 1.0000
7.500 1.2442 0.01251 0.00607 -0.0772 0.2118 1.0000
7.750 1.2601 0.01391 0.00694 -0.0758 0.1280 1.0000
8.000 1.2763 0.01528 0.00797 -0.0744 0.0780 1.0000
8.250 1.2898 0.01691 0.00923 -0.0725 0.0255 1.0000
8.500 1.3095 0.01775 0.01011 -0.0713 0.0209 1.0000
8.750 1.3301 0.01846 0.01092 -0.0703 0.0192 1.0000
9.000 1.3496 0.01922 0.01178 -0.0691 0.0180 1.0000
9.250 1.3672 0.02012 0.01278 -0.0677 0.0169 1.0000
9.500 1.3810 0.02130 0.01405 -0.0658 0.0160 1.0000
9.750 1.3892 0.02283 0.01572 -0.0632 0.0151 1.0000
10.000 1.4043 0.02367 0.01665 -0.0615 0.0146 1.0000
10.250 1.4148 0.02471 0.01778 -0.0591 0.0141 1.0000
10.500 1.4205 0.02589 0.01906 -0.0561 0.0137 1.0000
10.750 1.4248 0.02724 0.02051 -0.0533 0.0133 1.0000
11.000 1.4279 0.02877 0.02215 -0.0506 0.0130 1.0000
11.250 1.4300 0.03049 0.02397 -0.0482 0.0126 1.0000
11.500 1.4307 0.03247 0.02604 -0.0461 0.0124 1.0000
11.750 1.4297 0.03477 0.02842 -0.0442 0.0121 1.0000
12.000 1.4273 0.03738 0.03113 -0.0427 0.0119 1.0000
12.250 1.4233 0.04035 0.03419 -0.0413 0.0117 1.0000
12.500 1.4191 0.04348 0.03740 -0.0399 0.0115 1.0000
12.750 1.4162 0.04661 0.04060 -0.0380 0.0113 1.0000
13.000 1.4192 0.04911 0.04326 -0.0378 0.0112 1.0000
13.250 1.4212 0.05182 0.04611 -0.0378 0.0110 1.0000
13.500 1.4222 0.05472 0.04915 -0.0378 0.0108 1.0000
13.750 1.4220 0.05781 0.05238 -0.0379 0.0105 1.0000
14.000 1.4208 0.06105 0.05575 -0.0379 0.0104 1.0000
14.250 1.4187 0.06448 0.05932 -0.0381 0.0102 1.0000
14.500 1.4157 0.06808 0.06305 -0.0383 0.0101 1.0000
14.750 1.4117 0.07189 0.06700 -0.0386 0.0100 1.0000
15.000 1.4067 0.07596 0.07122 -0.0393 0.0099 1.0000
15.250 1.4007 0.08029 0.07570 -0.0402 0.0098 1.0000
15.500 1.3932 0.08494 0.08050 -0.0414 0.0098 1.0000
15.750 1.3849 0.08987 0.08558 -0.0429 0.0097 1.0000
16.000 1.3751 0.09519 0.09108 -0.0448 0.0097 1.0000
16.250 1.3641 0.10086 0.09691 -0.0470 0.0097 1.0000
16.500 1.3517 0.10695 0.10317 -0.0496 0.0097 1.0000
16.750 1.3386 0.11341 0.10980 -0.0527 0.0097 1.0000
17.000 1.3245 0.12028 0.11684 -0.0562 0.0098 1.0000
17.250 1.3095 0.12754 0.12427 -0.0601 0.0098 1.0000
17.500 1.2941 0.13516 0.13206 -0.0644 0.0099 1.0000
17.750 1.2782 0.14320 0.14026 -0.0692 0.0100 1.0000
18.000 1.2618 0.15173 0.14895 -0.0745 0.0101 1.0000
18.250 1.2449 0.16077 0.15815 -0.0803 0.0103 1.0000
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Polar data table (+)
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