DF102 (df102-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: DF102 (df102-il) Reynolds number: 50,000 Max Cl/Cd: 32.62 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-df102-il-50000-n5.txt Download as CSV file: xf-df102-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DF102
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4539 0.09961 0.09239 -0.0334 1.0000 0.0513
-10.000 -0.4591 0.09447 0.08733 -0.0358 1.0000 0.0509
-9.750 -0.4673 0.08881 0.08176 -0.0386 1.0000 0.0503
-9.500 -0.4800 0.08218 0.07524 -0.0422 1.0000 0.0497
-9.000 -0.5668 0.06335 0.05622 -0.0544 1.0000 0.0455
-8.750 -0.5834 0.05937 0.05208 -0.0537 1.0000 0.0455
-8.500 -0.5961 0.05563 0.04811 -0.0522 1.0000 0.0456
-8.250 -0.6016 0.05223 0.04455 -0.0504 1.0000 0.0461
-8.000 -0.6029 0.04915 0.04125 -0.0485 1.0000 0.0465
-7.750 -0.6011 0.04629 0.03817 -0.0464 1.0000 0.0472
-7.500 -0.5966 0.04364 0.03528 -0.0443 1.0000 0.0480
-7.250 -0.5895 0.04139 0.03280 -0.0423 1.0000 0.0497
-7.000 -0.5807 0.03922 0.03034 -0.0402 1.0000 0.0523
-6.750 -0.5701 0.03695 0.02764 -0.0382 1.0000 0.0549
-6.500 -0.5569 0.03478 0.02505 -0.0362 1.0000 0.0570
-6.250 -0.5427 0.03301 0.02320 -0.0344 1.0000 0.0592
-6.000 -0.5275 0.03157 0.02163 -0.0326 1.0000 0.0631
-5.750 -0.5107 0.03017 0.01987 -0.0309 1.0000 0.0684
-5.500 -0.4950 0.02884 0.01861 -0.0292 1.0000 0.0732
-5.250 -0.4776 0.02763 0.01723 -0.0275 1.0000 0.0792
-5.000 -0.4607 0.02654 0.01614 -0.0259 1.0000 0.0888
-4.750 -0.4429 0.02549 0.01506 -0.0245 1.0000 0.1038
-4.500 -0.4243 0.02446 0.01417 -0.0233 1.0000 0.1293
-4.250 -0.4051 0.02371 0.01361 -0.0223 1.0000 0.1794
-4.000 -0.3867 0.02339 0.01341 -0.0212 1.0000 0.2302
-3.750 -0.3649 0.02328 0.01333 -0.0208 0.9979 0.2792
-3.500 -0.3307 0.02318 0.01319 -0.0226 0.9899 0.3264
-3.250 -0.2942 0.02299 0.01293 -0.0247 0.9826 0.3613
-3.000 -0.2602 0.02272 0.01261 -0.0261 0.9744 0.3916
-2.750 -0.2245 0.02247 0.01235 -0.0279 0.9670 0.4235
-2.500 -0.1903 0.02221 0.01214 -0.0293 0.9587 0.4587
-2.250 -0.1575 0.02195 0.01199 -0.0304 0.9505 0.5009
-2.000 -0.1236 0.02168 0.01189 -0.0316 0.9426 0.5572
-1.750 -0.0952 0.02136 0.01187 -0.0314 0.9336 0.6294
-1.500 -0.0583 0.02106 0.01199 -0.0321 0.9271 0.7424
-1.250 0.0170 0.02105 0.01211 -0.0400 0.9250 0.9212
-1.000 0.0816 0.02117 0.01195 -0.0477 0.9193 1.0000
-0.750 0.1218 0.02130 0.01184 -0.0505 0.9112 1.0000
-0.500 0.1502 0.02145 0.01181 -0.0511 0.8994 1.0000
-0.250 0.1810 0.02160 0.01180 -0.0520 0.8885 1.0000
0.000 0.2196 0.02170 0.01176 -0.0542 0.8802 1.0000
0.250 0.2469 0.02186 0.01182 -0.0543 0.8684 1.0000
0.500 0.2738 0.02203 0.01189 -0.0542 0.8567 1.0000
0.750 0.3037 0.02217 0.01195 -0.0546 0.8459 1.0000
1.000 0.3387 0.02221 0.01195 -0.0557 0.8365 1.0000
1.250 0.3658 0.02229 0.01198 -0.0553 0.8230 1.0000
1.500 0.3979 0.02212 0.01177 -0.0553 0.8076 1.0000
1.750 0.4270 0.02185 0.01145 -0.0544 0.7879 1.0000
2.000 0.4555 0.02152 0.01108 -0.0533 0.7667 1.0000
2.250 0.4857 0.02119 0.01071 -0.0525 0.7476 1.0000
2.500 0.5101 0.02113 0.01063 -0.0511 0.7286 1.0000
2.750 0.5344 0.02107 0.01058 -0.0497 0.7087 1.0000
3.000 0.5609 0.02095 0.01043 -0.0485 0.6886 1.0000
3.250 0.5839 0.02096 0.01042 -0.0469 0.6653 1.0000
3.500 0.6088 0.02090 0.01034 -0.0454 0.6408 1.0000
3.750 0.6317 0.02094 0.01033 -0.0438 0.6129 1.0000
4.000 0.6534 0.02103 0.01036 -0.0419 0.5807 1.0000
4.250 0.6738 0.02120 0.01047 -0.0400 0.5436 1.0000
4.500 0.6936 0.02144 0.01058 -0.0379 0.5011 1.0000
4.750 0.7121 0.02183 0.01074 -0.0358 0.4525 1.0000
5.000 0.7294 0.02240 0.01101 -0.0337 0.4047 1.0000
5.250 0.7461 0.02314 0.01148 -0.0317 0.3639 1.0000
5.500 0.7631 0.02397 0.01205 -0.0300 0.3323 1.0000
5.750 0.7813 0.02482 0.01272 -0.0285 0.3085 1.0000
6.000 0.8004 0.02568 0.01345 -0.0272 0.2894 1.0000
6.250 0.8205 0.02656 0.01425 -0.0262 0.2736 1.0000
6.500 0.8421 0.02744 0.01509 -0.0253 0.2601 1.0000
6.750 0.8651 0.02833 0.01597 -0.0246 0.2485 1.0000
7.000 0.8884 0.02925 0.01685 -0.0240 0.2380 1.0000
7.250 0.9116 0.03018 0.01783 -0.0234 0.2280 1.0000
7.500 0.9358 0.03117 0.01892 -0.0230 0.2196 1.0000
7.750 0.9609 0.03219 0.01997 -0.0226 0.2126 1.0000
8.000 0.9843 0.03330 0.02123 -0.0221 0.2054 1.0000
8.250 1.0072 0.03438 0.02241 -0.0216 0.1987 1.0000
8.500 1.0292 0.03559 0.02376 -0.0209 0.1924 1.0000
8.750 1.0506 0.03688 0.02525 -0.0203 0.1869 1.0000
9.000 1.0748 0.03817 0.02660 -0.0200 0.1826 1.0000
9.250 1.0934 0.03973 0.02844 -0.0190 0.1781 1.0000
9.500 1.1098 0.04128 0.03029 -0.0179 0.1731 1.0000
9.750 1.1301 0.04260 0.03169 -0.0172 0.1687 1.0000
10.000 1.1456 0.04435 0.03368 -0.0160 0.1649 1.0000
10.250 1.1552 0.04648 0.03621 -0.0144 0.1615 1.0000
10.500 1.1659 0.04853 0.03855 -0.0129 0.1582 1.0000
10.750 1.1809 0.05024 0.04042 -0.0118 0.1548 1.0000
11.000 1.1929 0.05219 0.04256 -0.0106 0.1516 1.0000
11.250 1.1833 0.05507 0.04589 -0.0077 0.1487 1.0000
11.500 1.1748 0.05789 0.04903 -0.0051 0.1461 1.0000
11.750 1.1656 0.06069 0.05207 -0.0025 0.1440 1.0000
12.000 1.1566 0.06362 0.05519 -0.0005 0.1421 1.0000
12.250 1.1611 0.06588 0.05757 0.0007 0.1398 1.0000
12.500 1.1496 0.06927 0.06111 0.0019 0.1380 1.0000
12.750 1.1052 0.07560 0.06767 0.0021 0.1377 1.0000
13.000 1.0453 0.08538 0.07758 -0.0014 0.1378 1.0000
13.250 0.9460 0.10582 0.09794 -0.0138 0.1379 1.0000
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Polar data table (+)
Polar graphs
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