DAE-11 AIRFOIL (dae11-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: DAE-11 AIRFOIL (dae11-il) Reynolds number: 100,000 Max Cl/Cd: 32.62 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dae11-il-100000-n5.txt Download as CSV file: xf-dae11-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DAE-11 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.0516 0.10331 0.09760 -0.0760 0.7621 0.0515
-9.000 -0.0475 0.10099 0.09529 -0.0779 0.7597 0.0531
-8.750 -0.0483 0.09916 0.09348 -0.0807 0.7573 0.0541
-8.500 -0.0496 0.09709 0.09143 -0.0836 0.7551 0.0545
-8.250 -0.0475 0.09469 0.08910 -0.0865 0.7519 0.0547
-8.000 -0.0362 0.09081 0.08526 -0.0868 0.7496 0.0552
-7.750 -0.0203 0.08756 0.08200 -0.0860 0.7473 0.0562
-7.500 -0.0099 0.08493 0.07937 -0.0863 0.7448 0.0572
-7.250 -0.0020 0.08252 0.07695 -0.0869 0.7424 0.0585
-7.000 0.0034 0.08027 0.07470 -0.0878 0.7403 0.0607
-6.750 0.0039 0.07830 0.07278 -0.0897 0.7377 0.0630
-6.500 0.0047 0.07550 0.07002 -0.1007 0.7335 0.0654
-5.500 0.0555 0.05588 0.05006 -0.1139 0.7240 0.0375
-5.250 0.0723 0.05297 0.04709 -0.1162 0.7213 0.0367
-5.000 0.0909 0.04933 0.04331 -0.1195 0.7176 0.0358
-4.750 0.1121 0.04513 0.03884 -0.1229 0.7145 0.0349
-4.500 0.1354 0.04095 0.03423 -0.1256 0.7119 0.0343
-4.250 0.1603 0.03759 0.03040 -0.1274 0.7099 0.0345
-4.000 0.1866 0.03494 0.02721 -0.1285 0.7082 0.0361
-3.750 0.2124 0.03276 0.02449 -0.1292 0.7055 0.0371
-3.500 0.2366 0.03126 0.02258 -0.1295 0.7013 0.0375
-3.250 0.2623 0.02990 0.02085 -0.1295 0.6982 0.0382
-3.000 0.2882 0.02886 0.01964 -0.1295 0.6958 0.0392
-2.750 0.3150 0.02808 0.01871 -0.1295 0.6938 0.0415
-2.500 0.3429 0.02727 0.01763 -0.1293 0.6921 0.0446
-2.250 0.3668 0.02677 0.01704 -0.1290 0.6885 0.0466
-2.000 0.3891 0.02658 0.01687 -0.1287 0.6842 0.0489
-1.750 0.4143 0.02627 0.01646 -0.1284 0.6812 0.0537
-1.500 0.4406 0.02579 0.01599 -0.1282 0.6788 0.0591
-1.250 0.4680 0.02534 0.01544 -0.1279 0.6770 0.0667
-1.000 0.4961 0.02490 0.01497 -0.1278 0.6755 0.0798
-0.750 0.5126 0.02545 0.01567 -0.1272 0.6690 0.0984
-0.500 0.5371 0.02520 0.01564 -0.1271 0.6656 0.1570
-0.250 0.5636 0.02459 0.01564 -0.1272 0.6632 0.3466
0.000 0.5887 0.02390 0.01563 -0.1265 0.6614 0.5821
0.500 0.6344 0.02421 0.01647 -0.1253 0.6525 1.0000
0.750 0.6594 0.02451 0.01659 -0.1250 0.6492 1.0000
1.000 0.6873 0.02460 0.01650 -0.1249 0.6469 1.0000
1.250 0.7166 0.02460 0.01632 -0.1249 0.6452 1.0000
1.750 0.7516 0.02623 0.01781 -0.1233 0.6340 1.0000
2.000 0.7797 0.02627 0.01773 -0.1231 0.6317 1.0000
2.250 0.8095 0.02618 0.01753 -0.1231 0.6300 1.0000
2.750 0.8400 0.02799 0.01927 -0.1210 0.6180 1.0000
3.000 0.8691 0.02792 0.01913 -0.1209 0.6160 1.0000
3.250 0.8999 0.02774 0.01887 -0.1210 0.6145 1.0000
3.750 0.9256 0.02968 0.02081 -0.1183 0.6015 1.0000
4.000 0.9570 0.02940 0.02048 -0.1183 0.6000 1.0000
4.500 0.9790 0.03139 0.02250 -0.1152 0.5866 1.0000
4.750 1.0115 0.03101 0.02209 -0.1153 0.5851 1.0000
5.250 1.0282 0.03315 0.02426 -0.1116 0.5711 1.0000
5.500 1.0619 0.03255 0.02367 -0.1117 0.5699 1.0000
6.000 1.0683 0.03575 0.02693 -0.1078 0.5524 1.0000
6.500 1.1059 0.03659 0.02785 -0.1060 0.5419 1.0000
6.750 1.1393 0.03583 0.02711 -0.1059 0.5405 1.0000
7.250 1.1463 0.03925 0.03062 -0.1026 0.5217 1.0000
7.500 1.1608 0.04003 0.03148 -0.1015 0.5147 1.0000
7.750 1.1926 0.03926 0.03075 -0.1012 0.5125 1.0000
8.000 1.2251 0.03843 0.02997 -0.1010 0.5102 1.0000
8.500 1.2287 0.04228 0.03398 -0.0978 0.4891 1.0000
8.750 1.2544 0.04197 0.03374 -0.0972 0.4844 1.0000
9.000 1.2901 0.04073 0.03256 -0.0970 0.4817 1.0000
9.500 1.3251 0.04162 0.03362 -0.0951 0.4667 1.0000
9.750 1.3244 0.04382 0.03590 -0.0935 0.4548 1.0000
10.250 1.3625 0.04440 0.03665 -0.0918 0.4387 1.0000
10.500 1.3713 0.04572 0.03805 -0.0906 0.4282 1.0000
10.750 1.4051 0.04449 0.03687 -0.0901 0.4214 1.0000
11.000 1.4078 0.04640 0.03887 -0.0888 0.4091 1.0000
11.250 1.4185 0.04752 0.04008 -0.0877 0.3976 1.0000
11.500 1.4362 0.04790 0.04050 -0.0867 0.3866 1.0000
11.750 1.4557 0.04806 0.04069 -0.0858 0.3751 1.0000
12.000 1.4631 0.04950 0.04218 -0.0846 0.3619 1.0000
12.250 1.4687 0.05119 0.04393 -0.0835 0.3483 1.0000
12.500 1.4744 0.05290 0.04568 -0.0824 0.3344 1.0000
12.750 1.4797 0.05470 0.04752 -0.0814 0.3204 1.0000
13.000 1.4839 0.05667 0.04950 -0.0804 0.3058 1.0000
13.250 1.4872 0.05879 0.05164 -0.0795 0.2913 1.0000
13.500 1.4891 0.06112 0.05401 -0.0787 0.2767 1.0000
13.750 1.4904 0.06361 0.05651 -0.0779 0.2621 1.0000
14.000 1.4904 0.06632 0.05923 -0.0773 0.2477 1.0000
14.250 1.4896 0.06921 0.06213 -0.0768 0.2334 1.0000
14.500 1.4880 0.07227 0.06522 -0.0763 0.2194 1.0000
14.750 1.4857 0.07551 0.06847 -0.0761 0.2058 1.0000
15.000 1.4827 0.07892 0.07190 -0.0759 0.1925 1.0000
15.250 1.4792 0.08249 0.07550 -0.0759 0.1797 1.0000
15.500 1.4751 0.08620 0.07922 -0.0760 0.1677 1.0000
15.750 1.4704 0.09009 0.08313 -0.0762 0.1561 1.0000
16.000 1.4656 0.09411 0.08718 -0.0767 0.1448 1.0000
16.250 1.4609 0.09818 0.09131 -0.0772 0.1341 1.0000
16.500 1.4560 0.10234 0.09552 -0.0779 0.1243 1.0000
16.750 1.4504 0.10665 0.09985 -0.0787 0.1153 1.0000
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Polar data table (+)
Polar graphs
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