E180 (8.59%) (e180-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E180 (8.59%) (e180-il) Reynolds number: 100,000 Max Cl/Cd: 52.71 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e180-il-100000.txt Download as CSV file: xf-e180-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E180 (8.59%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4969 0.09927 0.09481 -0.0002 1.0000 0.0876
-8.250 -0.5040 0.09605 0.09169 -0.0052 1.0000 0.0902
-8.000 -0.5188 0.09270 0.08845 -0.0133 1.0000 0.0910
-7.750 -0.4906 0.08815 0.08388 -0.0062 1.0000 0.0972
-7.500 -0.4094 0.07415 0.07023 -0.0112 1.0000 0.1102
-7.250 -0.4115 0.07023 0.06638 -0.0133 1.0000 0.1147
-7.000 -0.4363 0.06540 0.06158 -0.0238 1.0000 0.1184
-6.750 -0.4232 0.06046 0.05672 -0.0219 1.0000 0.1216
-6.500 -0.4132 0.05659 0.05288 -0.0224 1.0000 0.1274
-6.250 -0.4600 0.06395 0.05980 -0.0254 1.0000 0.1277
-6.000 -0.4501 0.05953 0.05531 -0.0289 1.0000 0.1363
-5.750 -0.4386 0.05578 0.05141 -0.0319 1.0000 0.1485
-5.500 -0.4275 0.05284 0.04836 -0.0330 1.0000 0.1618
-5.250 -0.4213 0.05014 0.04583 -0.0304 1.0000 0.1652
-5.000 -0.4328 0.04894 0.04449 -0.0276 1.0000 0.1764
-4.750 -0.4027 0.03520 0.02885 -0.0304 0.9961 0.0633
-4.500 -0.3648 0.02998 0.02309 -0.0334 0.9871 0.0565
-4.250 -0.3222 0.02636 0.01841 -0.0354 0.9785 0.0523
-4.000 -0.2799 0.02347 0.01523 -0.0386 0.9712 0.0558
-3.750 -0.2378 0.02165 0.01305 -0.0411 0.9627 0.0624
-3.500 -0.1932 0.01937 0.01068 -0.0439 0.9566 0.0708
-3.250 -0.1579 0.01783 0.00923 -0.0452 0.9464 0.0999
-3.000 -0.1264 0.01625 0.00810 -0.0461 0.9364 0.1873
-2.750 -0.1008 0.01426 0.00753 -0.0461 0.9271 0.4431
-2.500 -0.0407 0.01277 0.00744 -0.0490 0.9252 0.9046
-2.250 0.0626 0.01250 0.00661 -0.0629 0.9270 1.0000
-2.000 0.0881 0.01258 0.00640 -0.0628 0.9128 1.0000
-1.750 0.1118 0.01272 0.00630 -0.0623 0.9001 1.0000
-1.500 0.1337 0.01289 0.00627 -0.0614 0.8880 1.0000
-1.250 0.1551 0.01310 0.00630 -0.0603 0.8762 1.0000
-1.000 0.1769 0.01332 0.00635 -0.0594 0.8654 1.0000
-0.750 0.1986 0.01355 0.00643 -0.0582 0.8556 1.0000
-0.500 0.2204 0.01378 0.00652 -0.0570 0.8464 1.0000
-0.250 0.2431 0.01406 0.00669 -0.0563 0.8364 1.0000
0.000 0.2655 0.01432 0.00685 -0.0552 0.8278 1.0000
0.250 0.2882 0.01458 0.00701 -0.0542 0.8192 1.0000
0.500 0.3115 0.01489 0.00726 -0.0536 0.8100 1.0000
0.750 0.3340 0.01514 0.00742 -0.0523 0.8028 1.0000
1.000 0.3577 0.01548 0.00774 -0.0518 0.7933 1.0000
1.250 0.3811 0.01580 0.00803 -0.0510 0.7852 1.0000
1.500 0.4043 0.01608 0.00827 -0.0500 0.7772 1.0000
1.750 0.4280 0.01646 0.00866 -0.0495 0.7680 1.0000
2.000 0.4510 0.01667 0.00883 -0.0480 0.7612 1.0000
2.250 0.4748 0.01706 0.00928 -0.0476 0.7509 1.0000
2.500 0.4982 0.01739 0.00964 -0.0467 0.7418 1.0000
2.750 0.5216 0.01756 0.00980 -0.0453 0.7337 1.0000
3.000 0.5451 0.01790 0.01020 -0.0446 0.7228 1.0000
3.250 0.5685 0.01817 0.01052 -0.0435 0.7122 1.0000
3.500 0.5920 0.01827 0.01069 -0.0420 0.7025 1.0000
3.750 0.6156 0.01835 0.01081 -0.0406 0.6917 1.0000
4.000 0.6391 0.01850 0.01105 -0.0394 0.6792 1.0000
4.250 0.6627 0.01856 0.01119 -0.0380 0.6663 1.0000
4.500 0.6865 0.01853 0.01128 -0.0365 0.6527 1.0000
4.750 0.7104 0.01840 0.01123 -0.0349 0.6383 1.0000
5.000 0.7345 0.01818 0.01109 -0.0331 0.6229 1.0000
5.250 0.7590 0.01787 0.01085 -0.0313 0.6067 1.0000
5.500 0.7827 0.01766 0.01084 -0.0298 0.5855 1.0000
5.750 0.8071 0.01719 0.01042 -0.0279 0.5636 1.0000
6.000 0.8300 0.01666 0.01002 -0.0259 0.5282 1.0000
6.250 0.8513 0.01615 0.00947 -0.0237 0.4693 1.0000
6.500 0.8685 0.01648 0.00936 -0.0215 0.3585 1.0000
6.750 0.8783 0.01840 0.01042 -0.0195 0.2169 1.0000
7.000 0.8801 0.02181 0.01276 -0.0170 0.0994 1.0000
7.250 0.8919 0.02392 0.01467 -0.0148 0.0752 1.0000
7.500 0.9078 0.02561 0.01632 -0.0132 0.0644 1.0000
7.750 0.9256 0.02778 0.01829 -0.0118 0.0586 1.0000
8.000 0.9494 0.02960 0.02030 -0.0106 0.0555 1.0000
8.250 0.9742 0.03184 0.02270 -0.0097 0.0531 1.0000
8.500 0.9984 0.03442 0.02555 -0.0087 0.0516 1.0000
8.750 1.0190 0.03697 0.02826 -0.0079 0.0491 1.0000
9.000 1.0365 0.04148 0.03295 -0.0073 0.0469 1.0000
9.250 1.0507 0.04494 0.03686 -0.0060 0.0468 1.0000
9.500 1.0625 0.04925 0.04159 -0.0047 0.0471 1.0000
9.750 1.0724 0.05162 0.04445 -0.0028 0.0480 1.0000
10.000 1.0599 0.05613 0.04984 0.0001 0.0509 1.0000
10.250 1.0464 0.06121 0.05539 0.0019 0.0533 1.0000
10.500 1.0331 0.06573 0.06017 0.0032 0.0551 1.0000
10.750 1.0184 0.06995 0.06454 0.0043 0.0563 1.0000
11.000 1.0165 0.07481 0.06955 0.0046 0.0602 1.0000
11.250 0.9822 0.07932 0.07428 0.0032 0.0608 1.0000
11.500 0.9483 0.08556 0.08069 -0.0007 0.0612 1.0000
11.750 0.9125 0.09401 0.08925 -0.0071 0.0618 1.0000
12.000 0.7986 0.09336 0.08884 -0.0042 0.0569 1.0000
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Polar data table (+)
Polar graphs
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