DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: DU 86-137/25 AIRFOIL (du861372-il) Reynolds number: 50,000 Max Cl/Cd: 28.94 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du861372-il-50000.txt Download as CSV file: xf-du861372-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: DU 86-137/25 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5954 0.10565 0.10048 -0.0237 1.0000 0.1604
-11.000 -0.6223 0.09386 0.08876 -0.0317 1.0000 0.1384
-10.750 -0.6967 0.08322 0.07816 -0.0393 1.0000 0.1328
-10.500 -0.7489 0.07867 0.07350 -0.0396 1.0000 0.1316
-10.250 -0.7369 0.07336 0.06814 -0.0400 1.0000 0.1248
-10.000 -0.7625 0.06944 0.06411 -0.0381 1.0000 0.1222
-9.750 -0.7931 0.06556 0.05994 -0.0353 1.0000 0.1190
-9.500 -0.8236 0.06277 0.05654 -0.0312 1.0000 0.1152
-9.250 -0.8101 0.05834 0.05208 -0.0306 1.0000 0.1122
-9.000 -0.8102 0.05491 0.04838 -0.0284 1.0000 0.1098
-8.750 -0.8028 0.05115 0.04419 -0.0273 0.9717 0.1073
-8.500 -0.7890 0.04743 0.03987 -0.0268 0.9508 0.1051
-8.250 -0.7694 0.04418 0.03594 -0.0263 0.9381 0.1032
-8.000 -0.7404 0.04127 0.03255 -0.0267 0.9305 0.1018
-7.750 -0.7046 0.03834 0.02939 -0.0278 0.9256 0.1007
-7.500 -0.6598 0.03572 0.02655 -0.0296 0.9235 0.1000
-7.250 -0.5992 0.03359 0.02426 -0.0325 0.9262 0.1005
-7.000 -0.5421 0.03225 0.02285 -0.0348 0.9299 0.1026
-6.750 -0.5133 0.03116 0.02178 -0.0348 0.9249 0.1057
-6.500 -0.4912 0.03010 0.02067 -0.0344 0.9186 0.1103
-6.250 -0.4731 0.02900 0.01951 -0.0336 0.9121 0.1174
-6.000 -0.4587 0.02787 0.01840 -0.0323 0.9046 0.1322
-5.750 -0.4496 0.02636 0.01711 -0.0305 0.8986 0.1715
-5.500 -0.4597 0.02408 0.01607 -0.0263 0.8903 0.3185
-5.250 -0.4264 0.02571 0.01905 -0.0215 0.8891 0.6001
-5.000 -0.4054 0.02676 0.01983 -0.0186 0.8846 0.6462
-4.750 -0.3851 0.02795 0.02079 -0.0155 0.8807 0.6843
-4.500 -0.3489 0.02924 0.02183 -0.0147 0.8790 0.7064
-4.250 -0.3159 0.03029 0.02265 -0.0137 0.8762 0.7288
-4.000 -0.2907 0.03095 0.02310 -0.0122 0.8718 0.7507
-3.750 -0.2470 0.03178 0.02372 -0.0130 0.8694 0.7706
-3.500 -0.2106 0.03188 0.02361 -0.0141 0.8655 0.7841
-3.250 -0.1652 0.03193 0.02344 -0.0166 0.8628 0.7962
-3.000 -0.1340 0.03187 0.02323 -0.0172 0.8581 0.8091
-2.750 -0.1103 0.03173 0.02297 -0.0169 0.8533 0.8219
-2.500 -0.0732 0.03172 0.02283 -0.0184 0.8510 0.8379
-2.250 -0.0328 0.03163 0.02263 -0.0206 0.8492 0.8543
-2.000 0.0088 0.03128 0.02217 -0.0235 0.8473 0.8654
-1.750 0.0480 0.03096 0.02176 -0.0260 0.8456 0.8791
-1.500 0.0905 0.03077 0.02150 -0.0289 0.8441 0.9015
-1.250 0.1603 0.03001 0.02069 -0.0368 0.8449 0.9319
-1.000 0.2034 0.02941 0.02006 -0.0408 0.8427 0.9473
-0.750 0.3227 0.02684 0.01750 -0.0599 0.8475 1.0000
-0.500 0.3423 0.02674 0.01738 -0.0598 0.8431 1.0000
-0.250 0.3608 0.02670 0.01737 -0.0595 0.8374 1.0000
0.000 0.3801 0.02667 0.01735 -0.0593 0.8325 1.0000
0.250 0.4003 0.02666 0.01735 -0.0591 0.8284 1.0000
0.500 0.4178 0.02677 0.01750 -0.0586 0.8225 1.0000
0.750 0.4359 0.02689 0.01766 -0.0581 0.8170 1.0000
1.000 0.4553 0.02699 0.01779 -0.0576 0.8125 1.0000
1.250 0.4729 0.02719 0.01807 -0.0570 0.8063 1.0000
1.500 0.4907 0.02737 0.01830 -0.0562 0.7991 1.0000
1.750 0.5100 0.02746 0.01843 -0.0553 0.7921 1.0000
2.000 0.5254 0.02767 0.01872 -0.0539 0.7824 1.0000
2.250 0.5427 0.02783 0.01897 -0.0527 0.7743 1.0000
2.500 0.5587 0.02799 0.01922 -0.0511 0.7650 1.0000
2.750 0.5728 0.02822 0.01956 -0.0493 0.7544 1.0000
3.000 0.5902 0.02823 0.01967 -0.0476 0.7451 1.0000
3.250 0.6031 0.02842 0.02002 -0.0455 0.7333 1.0000
3.500 0.6150 0.02860 0.02036 -0.0433 0.7205 1.0000
3.750 0.6279 0.02860 0.02050 -0.0409 0.7069 1.0000
4.000 0.6404 0.02838 0.02044 -0.0381 0.6900 1.0000
4.250 0.6536 0.02786 0.02008 -0.0349 0.6696 1.0000
4.500 0.6653 0.02725 0.01966 -0.0314 0.6446 1.0000
4.750 0.6775 0.02641 0.01897 -0.0275 0.6109 1.0000
5.000 0.6930 0.02529 0.01786 -0.0234 0.5581 1.0000
5.250 0.7085 0.02448 0.01644 -0.0186 0.4671 1.0000
5.500 0.7115 0.02541 0.01646 -0.0137 0.3925 1.0000
5.750 0.7116 0.02640 0.01717 -0.0096 0.3294 1.0000
6.000 0.7879 0.03681 0.02578 -0.0165 0.2491 1.0000
6.250 0.7945 0.03780 0.02737 -0.0132 0.2288 1.0000
6.500 0.8049 0.03862 0.02843 -0.0106 0.2106 1.0000
6.750 0.8144 0.03925 0.02940 -0.0076 0.1957 1.0000
7.000 0.8248 0.03989 0.03019 -0.0049 0.1831 1.0000
7.250 0.8336 0.03973 0.02998 -0.0021 0.1733 1.0000
7.500 0.8433 0.04208 0.03275 0.0007 0.1641 1.0000
7.750 0.8523 0.04282 0.03342 0.0034 0.1570 1.0000
8.000 0.8537 0.04541 0.03651 0.0070 0.1499 1.0000
8.250 0.8605 0.04676 0.03791 0.0099 0.1442 1.0000
8.500 0.8633 0.04925 0.04051 0.0130 0.1411 1.0000
8.750 0.8537 0.05210 0.04380 0.0177 0.1396 1.0000
9.000 0.8416 0.05481 0.04685 0.0224 0.1386 1.0000
9.250 0.8274 0.05765 0.04997 0.0269 0.1373 1.0000
9.500 0.8148 0.06101 0.05360 0.0302 0.1368 1.0000
9.750 0.8011 0.06468 0.05752 0.0327 0.1364 1.0000
10.000 0.7853 0.06860 0.06163 0.0346 0.1367 1.0000
10.250 0.7670 0.07263 0.06579 0.0361 0.1377 1.0000
10.500 0.7475 0.07675 0.06998 0.0372 0.1389 1.0000
10.750 0.7361 0.08147 0.07474 0.0371 0.1404 1.0000
11.000 0.6223 0.09581 0.08902 0.0263 0.1668 1.0000
11.250 0.6221 0.10219 0.09539 0.0239 0.1720 1.0000
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Polar data table (+)
Polar graphs
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