E182 (8.47%) (e182-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E182 (8.47%) (e182-il) Reynolds number: 100,000 Max Cl/Cd: 48.5 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e182-il-100000.txt Download as CSV file: xf-e182-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E182 (8.47%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5630 0.09066 0.08641 0.0064 1.0000 0.1046
-7.750 -0.5861 0.08626 0.08207 -0.0055 1.0000 0.1079
-7.500 -0.5760 0.08112 0.07699 -0.0048 1.0000 0.1103
-7.250 -0.5609 0.07794 0.07384 -0.0031 1.0000 0.1142
-7.000 -0.5735 0.07275 0.06839 -0.0145 1.0000 0.1227
-6.750 -0.5518 0.06872 0.06457 -0.0109 1.0000 0.1259
-6.500 -0.5488 0.06439 0.05998 -0.0166 1.0000 0.1372
-6.250 -0.5294 0.06072 0.05647 -0.0148 1.0000 0.1412
-6.000 -0.5174 0.05676 0.05240 -0.0171 1.0000 0.1536
-5.750 -0.5020 0.05347 0.04904 -0.0180 1.0000 0.1682
-5.500 -0.4793 0.04027 0.03412 -0.0233 1.0000 0.0819
-5.250 -0.4566 0.03523 0.02855 -0.0227 1.0000 0.0667
-5.000 -0.4402 0.03175 0.02488 -0.0220 1.0000 0.0641
-4.750 -0.4335 0.02929 0.02207 -0.0191 1.0000 0.0610
-4.500 -0.4264 0.02697 0.01918 -0.0159 1.0000 0.0578
-4.250 -0.3954 0.02461 0.01623 -0.0164 0.9940 0.0561
-4.000 -0.3521 0.02208 0.01338 -0.0193 0.9852 0.0568
-3.750 -0.3092 0.02014 0.01133 -0.0221 0.9765 0.0601
-3.500 -0.2649 0.01854 0.00965 -0.0253 0.9687 0.0710
-3.250 -0.2253 0.01698 0.00818 -0.0274 0.9595 0.0951
-3.000 -0.1997 0.01431 0.00706 -0.0278 0.9485 0.3403
-2.750 -0.1546 0.01238 0.00720 -0.0286 0.9455 0.8421
-2.500 -0.0358 0.01246 0.00674 -0.0436 0.9551 0.9897
-2.250 0.0162 0.01230 0.00621 -0.0490 0.9443 1.0000
-2.000 0.0445 0.01237 0.00604 -0.0497 0.9280 1.0000
-1.750 0.0680 0.01251 0.00597 -0.0493 0.9130 1.0000
-1.500 0.0898 0.01267 0.00595 -0.0485 0.8995 1.0000
-1.250 0.1109 0.01286 0.00598 -0.0473 0.8875 1.0000
-1.000 0.1320 0.01306 0.00603 -0.0462 0.8759 1.0000
-0.750 0.1538 0.01328 0.00613 -0.0453 0.8648 1.0000
-0.500 0.1755 0.01352 0.00626 -0.0443 0.8547 1.0000
-0.250 0.1961 0.01375 0.00638 -0.0428 0.8458 1.0000
0.000 0.2195 0.01401 0.00657 -0.0423 0.8356 1.0000
0.250 0.2422 0.01429 0.00677 -0.0414 0.8264 1.0000
0.500 0.2637 0.01454 0.00695 -0.0400 0.8182 1.0000
0.750 0.2877 0.01484 0.00723 -0.0396 0.8084 1.0000
1.000 0.3103 0.01514 0.00748 -0.0386 0.8001 1.0000
1.250 0.3331 0.01541 0.00773 -0.0376 0.7913 1.0000
1.500 0.3567 0.01575 0.00807 -0.0370 0.7818 1.0000
1.750 0.3785 0.01599 0.00829 -0.0355 0.7740 1.0000
2.000 0.4021 0.01630 0.00865 -0.0348 0.7636 1.0000
2.250 0.4252 0.01662 0.00899 -0.0339 0.7535 1.0000
2.500 0.4471 0.01682 0.00920 -0.0323 0.7446 1.0000
2.750 0.4698 0.01705 0.00947 -0.0311 0.7339 1.0000
3.000 0.4927 0.01730 0.00981 -0.0299 0.7222 1.0000
3.250 0.5152 0.01748 0.01005 -0.0285 0.7104 1.0000
3.500 0.5374 0.01758 0.01020 -0.0268 0.6985 1.0000
3.750 0.5596 0.01760 0.01026 -0.0249 0.6863 1.0000
4.000 0.5819 0.01755 0.01027 -0.0230 0.6733 1.0000
4.250 0.6046 0.01750 0.01033 -0.0212 0.6584 1.0000
4.500 0.6275 0.01740 0.01034 -0.0195 0.6416 1.0000
4.750 0.6505 0.01720 0.01025 -0.0176 0.6237 1.0000
5.000 0.6736 0.01688 0.01001 -0.0155 0.6052 1.0000
5.250 0.6969 0.01657 0.00986 -0.0136 0.5821 1.0000
5.500 0.7192 0.01584 0.00915 -0.0110 0.5469 1.0000
5.750 0.7406 0.01527 0.00855 -0.0087 0.4799 1.0000
6.000 0.7590 0.01565 0.00840 -0.0067 0.3509 1.0000
6.250 0.7661 0.01866 0.00993 -0.0051 0.1340 1.0000
6.500 0.7761 0.02160 0.01221 -0.0032 0.0678 1.0000
6.750 0.7923 0.02337 0.01393 -0.0015 0.0584 1.0000
7.000 0.8113 0.02495 0.01551 0.0000 0.0531 1.0000
7.250 0.8313 0.02722 0.01765 0.0013 0.0500 1.0000
7.500 0.8550 0.02922 0.01982 0.0025 0.0481 1.0000
7.750 0.8780 0.03113 0.02201 0.0035 0.0455 1.0000
8.000 0.9000 0.03340 0.02453 0.0045 0.0435 1.0000
8.250 0.9204 0.03634 0.02784 0.0057 0.0435 1.0000
8.500 0.9373 0.03974 0.03172 0.0070 0.0442 1.0000
8.750 0.9500 0.04365 0.03612 0.0084 0.0454 1.0000
9.000 0.9591 0.04779 0.04068 0.0096 0.0469 1.0000
9.250 0.9654 0.05244 0.04563 0.0106 0.0484 1.0000
9.500 0.9700 0.05625 0.04994 0.0121 0.0517 1.0000
9.750 0.9455 0.06249 0.05685 0.0134 0.0566 1.0000
10.000 0.9456 0.06795 0.06250 0.0139 0.0634 1.0000
10.250 0.9100 0.07217 0.06700 0.0140 0.0648 1.0000
10.500 0.8770 0.07788 0.07286 0.0111 0.0656 1.0000
10.750 0.8466 0.08500 0.08008 0.0060 0.0661 1.0000
11.000 0.8126 0.09552 0.09062 -0.0024 0.0675 1.0000
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Polar data table (+)
Polar graphs
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