DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: DU 86-137/25 AIRFOIL (du861372-il) Reynolds number: 50,000 Max Cl/Cd: 23.77 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du861372-il-50000-n5.txt Download as CSV file: xf-du861372-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6866 0.10343 0.09567 -0.0271 0.4042 0.0589
-12.500 -0.7255 0.09374 0.08592 -0.0337 0.4045 0.0585
-12.250 -0.7604 0.08671 0.07879 -0.0373 0.4047 0.0583
-12.000 -0.7760 0.08188 0.07383 -0.0384 0.4051 0.0579
-11.750 -0.7921 0.07748 0.06930 -0.0389 0.4055 0.0576
-11.500 -0.8078 0.07336 0.06502 -0.0386 0.4061 0.0571
-11.250 -0.8225 0.06953 0.06099 -0.0377 0.4065 0.0566
-11.000 -0.8349 0.06606 0.05730 -0.0362 0.4071 0.0561
-10.750 -0.8459 0.06275 0.05368 -0.0340 0.4076 0.0554
-10.500 -0.8539 0.05958 0.05019 -0.0315 0.4081 0.0547
-10.250 -0.8548 0.05632 0.04655 -0.0294 0.4086 0.0540
-10.000 -0.8491 0.05336 0.04322 -0.0278 0.4090 0.0539
-9.750 -0.8375 0.05064 0.04016 -0.0265 0.4096 0.0541
-9.500 -0.8205 0.04796 0.03712 -0.0256 0.4099 0.0540
-9.250 -0.7959 0.04531 0.03409 -0.0254 0.4105 0.0534
-8.750 -0.7128 0.04073 0.02885 -0.0280 0.4114 0.0516
-8.500 -0.6721 0.03934 0.02728 -0.0289 0.4124 0.0510
-8.250 -0.6423 0.03823 0.02600 -0.0286 0.4140 0.0506
-8.000 -0.6205 0.03711 0.02473 -0.0277 0.4156 0.0504
-7.750 -0.6026 0.03599 0.02348 -0.0267 0.4176 0.0502
-7.500 -0.5862 0.03491 0.02224 -0.0255 0.4198 0.0504
-7.250 -0.5706 0.03386 0.02107 -0.0243 0.4215 0.0513
-7.000 -0.5551 0.03287 0.01997 -0.0231 0.4229 0.0520
-6.750 -0.5397 0.03191 0.01896 -0.0219 0.4244 0.0530
-6.500 -0.5240 0.03105 0.01800 -0.0206 0.4259 0.0537
-6.250 -0.5084 0.03022 0.01709 -0.0192 0.4313 0.0543
-6.000 -0.4922 0.02940 0.01620 -0.0179 0.4444 0.0554
-5.750 -0.4752 0.02862 0.01542 -0.0166 0.4580 0.0578
-5.500 -0.4563 0.02802 0.01470 -0.0156 0.4642 0.0684
-5.250 -0.4368 0.02753 0.01403 -0.0146 0.4646 0.0754
-5.000 -0.4178 0.02693 0.01339 -0.0136 0.4721 0.0805
-4.750 -0.4020 0.02601 0.01274 -0.0125 0.4843 0.0961
-4.500 -0.3819 0.02536 0.01226 -0.0118 0.5059 0.1542
-4.250 -0.3581 0.02487 0.01194 -0.0119 0.5480 0.1646
-4.000 -0.3320 0.02443 0.01183 -0.0130 0.6410 0.1738
-3.750 -0.3117 0.02405 0.01145 -0.0123 0.6539 0.1856
-3.250 -0.2958 0.02176 0.01073 -0.0072 0.6606 0.4332
-3.000 -0.2679 0.02189 0.01143 -0.0060 0.6646 0.5262
-2.750 -0.2353 0.02237 0.01213 -0.0056 0.6677 0.5874
-2.500 -0.2119 0.02245 0.01218 -0.0047 0.6683 0.6164
-2.250 -0.1894 0.02254 0.01225 -0.0037 0.6683 0.6414
-2.000 -0.1695 0.02258 0.01224 -0.0025 0.6671 0.6626
-1.750 -0.1493 0.02258 0.01220 -0.0015 0.6654 0.6784
-1.500 -0.1291 0.02255 0.01210 -0.0005 0.6630 0.6908
-1.250 -0.1107 0.02245 0.01195 0.0006 0.6593 0.7030
-1.000 -0.0895 0.02254 0.01201 0.0017 0.6549 0.7157
-0.750 -0.0708 0.02268 0.01214 0.0032 0.6504 0.7335
-0.500 -0.0496 0.02276 0.01221 0.0042 0.6447 0.7435
-0.250 -0.0306 0.02274 0.01214 0.0054 0.6387 0.7526
0.000 -0.0083 0.02280 0.01220 0.0062 0.6321 0.7597
0.250 0.0122 0.02281 0.01219 0.0073 0.6231 0.7677
0.500 0.0332 0.02285 0.01222 0.0084 0.6130 0.7762
0.750 0.0528 0.02300 0.01237 0.0102 0.6028 0.7913
1.000 0.0750 0.02331 0.01273 0.0119 0.5946 0.8098
1.250 0.0973 0.02346 0.01292 0.0132 0.5890 0.8223
1.500 0.1208 0.02353 0.01304 0.0140 0.5852 0.8305
1.750 0.1418 0.02358 0.01313 0.0151 0.5809 0.8392
2.000 0.1683 0.02377 0.01341 0.0158 0.5766 0.8534
2.250 0.1948 0.02391 0.01361 0.0164 0.5710 0.8674
2.500 0.2290 0.02408 0.01390 0.0158 0.5645 0.8848
2.750 0.2872 0.02441 0.01437 0.0114 0.5571 0.9138
3.000 0.3804 0.02440 0.01452 -0.0001 0.5442 0.9368
3.250 0.4033 0.02424 0.01435 0.0006 0.5277 0.9416
3.500 0.4292 0.02408 0.01416 0.0008 0.5093 0.9457
3.750 0.4585 0.02396 0.01401 0.0003 0.4883 0.9494
4.000 0.4828 0.02397 0.01393 0.0006 0.4657 0.9539
4.250 0.5047 0.02408 0.01401 0.0012 0.4456 0.9584
4.500 0.5323 0.02422 0.01418 0.0006 0.4262 0.9622
4.750 0.5551 0.02453 0.01439 0.0010 0.4083 0.9667
5.000 0.5749 0.02504 0.01469 0.0018 0.3889 0.9712
5.250 0.5986 0.02561 0.01522 0.0017 0.3644 0.9753
5.500 0.6174 0.02597 0.01567 0.0021 0.3074 0.9809
5.750 0.6587 0.02896 0.01691 0.0003 0.2845 0.9795
6.000 0.6969 0.03148 0.01968 -0.0018 0.2543 0.9809
6.250 0.7121 0.03199 0.02095 -0.0009 0.2299 0.9864
6.500 0.7188 0.03118 0.02123 0.0013 0.1903 0.9949
6.750 0.7298 0.03122 0.02143 0.0027 0.1653 1.0000
7.000 0.7236 0.03153 0.02169 0.0073 0.1541 1.0000
7.250 0.7184 0.03218 0.02229 0.0117 0.1412 1.0000
7.500 0.7175 0.03299 0.02306 0.0157 0.1263 1.0000
7.750 0.7189 0.03379 0.02384 0.0194 0.1134 1.0000
8.000 0.7195 0.03461 0.02464 0.0232 0.1048 1.0000
8.250 0.7230 0.03541 0.02546 0.0266 0.0959 1.0000
8.500 0.7279 0.03633 0.02636 0.0296 0.0884 1.0000
8.750 0.7399 0.03745 0.02755 0.0317 0.0813 1.0000
9.000 0.7534 0.03892 0.02891 0.0332 0.0759 1.0000
9.250 0.7737 0.04047 0.03077 0.0341 0.0690 1.0000
9.500 0.7886 0.04206 0.03242 0.0351 0.0644 1.0000
9.750 0.8073 0.04441 0.03475 0.0356 0.0615 1.0000
10.000 0.8217 0.04692 0.03772 0.0366 0.0592 1.0000
10.250 0.8292 0.04948 0.04066 0.0380 0.0567 1.0000
10.500 0.8314 0.05191 0.04337 0.0396 0.0544 1.0000
10.750 0.8305 0.05429 0.04596 0.0413 0.0525 1.0000
11.000 0.8283 0.05684 0.04868 0.0427 0.0511 1.0000
11.250 0.8236 0.05975 0.05177 0.0438 0.0502 1.0000
11.500 0.8151 0.06314 0.05536 0.0444 0.0496 1.0000
11.750 0.8032 0.06697 0.05938 0.0446 0.0492 1.0000
12.000 0.7854 0.07144 0.06406 0.0441 0.0493 1.0000
12.250 0.7607 0.07700 0.06985 0.0423 0.0495 1.0000
12.500 0.7193 0.08589 0.07898 0.0374 0.0505 1.0000
12.750 0.6563 0.10354 0.09670 0.0253 0.0537 1.0000
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Polar data table (+)
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