E180 (8.59%) (e180-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E180 (8.59%) (e180-il) Reynolds number: 50,000 Max Cl/Cd: 35.47 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e180-il-50000.txt Download as CSV file: xf-e180-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4757 0.09610 0.09000 0.0049 1.0000 0.2496
-7.500 -0.4691 0.09272 0.08669 0.0050 1.0000 0.2653
-7.250 -0.4645 0.08953 0.08358 0.0049 1.0000 0.2826
-7.000 -0.4620 0.08652 0.08065 0.0047 1.0000 0.2982
-6.750 -0.4693 0.08427 0.07853 0.0038 1.0000 0.3152
-6.500 -0.4561 0.08019 0.07451 0.0049 1.0000 0.3331
-6.250 -0.3557 0.06384 0.05863 0.0007 1.0000 0.3635
-6.000 -0.3537 0.06045 0.05529 0.0014 1.0000 0.3839
-5.750 -0.4338 0.07054 0.06509 0.0075 1.0000 0.4039
-5.250 -0.4138 0.04851 0.04143 -0.0354 1.0000 0.1329
-5.000 -0.4010 0.04391 0.03649 -0.0348 1.0000 0.1198
-4.750 -0.3906 0.04090 0.03334 -0.0330 1.0000 0.1150
-4.500 -0.3816 0.03792 0.02997 -0.0311 1.0000 0.1104
-4.250 -0.3695 0.03511 0.02631 -0.0291 1.0000 0.1057
-4.000 -0.3555 0.03275 0.02358 -0.0274 1.0000 0.1060
-3.750 -0.3409 0.03089 0.02168 -0.0259 1.0000 0.1125
-3.500 -0.3225 0.02911 0.01931 -0.0244 1.0000 0.1183
-3.250 -0.3030 0.02712 0.01718 -0.0232 1.0000 0.1258
-3.000 -0.2830 0.02566 0.01550 -0.0220 1.0000 0.1442
-2.750 -0.2609 0.02408 0.01389 -0.0210 1.0000 0.1757
-2.500 -0.2374 0.02244 0.01256 -0.0202 1.0000 0.2392
-2.250 -0.1610 0.01750 0.01061 -0.0248 1.0000 1.0000
-2.000 -0.1486 0.01772 0.01028 -0.0233 1.0000 1.0000
-1.750 -0.1349 0.01798 0.01004 -0.0220 1.0000 1.0000
-1.500 -0.1202 0.01827 0.00995 -0.0209 1.0000 1.0000
-1.250 -0.1046 0.01860 0.00993 -0.0199 1.0000 1.0000
-1.000 -0.0884 0.01895 0.00998 -0.0191 1.0000 1.0000
-0.750 -0.0599 0.01948 0.01018 -0.0207 0.9956 1.0000
-0.500 -0.0181 0.02020 0.01054 -0.0247 0.9857 1.0000
-0.250 0.0208 0.02091 0.01098 -0.0282 0.9759 1.0000
0.000 0.0600 0.02165 0.01150 -0.0316 0.9664 1.0000
0.250 0.1004 0.02244 0.01207 -0.0351 0.9570 1.0000
0.500 0.1321 0.02313 0.01262 -0.0371 0.9469 1.0000
0.750 0.1652 0.02389 0.01326 -0.0393 0.9375 1.0000
1.000 0.2040 0.02472 0.01398 -0.0424 0.9280 1.0000
1.250 0.2321 0.02547 0.01467 -0.0436 0.9180 1.0000
1.500 0.2599 0.02628 0.01542 -0.0447 0.9082 1.0000
1.750 0.2930 0.02714 0.01627 -0.0467 0.8985 1.0000
2.000 0.3258 0.02801 0.01714 -0.0486 0.8883 1.0000
2.250 0.3483 0.02888 0.01801 -0.0487 0.8775 1.0000
2.500 0.3746 0.02979 0.01895 -0.0494 0.8666 1.0000
2.750 0.4045 0.03073 0.01994 -0.0507 0.8553 1.0000
3.000 0.4372 0.03166 0.02099 -0.0522 0.8435 1.0000
3.250 0.4716 0.03258 0.02202 -0.0539 0.8310 1.0000
3.500 0.5013 0.03350 0.02305 -0.0548 0.8175 1.0000
3.750 0.5312 0.03440 0.02408 -0.0555 0.8030 1.0000
4.000 0.5536 0.03535 0.02521 -0.0550 0.7873 1.0000
4.250 0.5767 0.03629 0.02630 -0.0546 0.7705 1.0000
4.500 0.6063 0.03704 0.02724 -0.0545 0.7523 1.0000
4.750 0.6487 0.03726 0.02774 -0.0550 0.7336 1.0000
5.000 0.6673 0.03806 0.02877 -0.0533 0.7120 1.0000
5.250 0.7125 0.03739 0.02844 -0.0522 0.6908 1.0000
5.500 0.7357 0.03747 0.02877 -0.0497 0.6656 1.0000
5.750 0.7662 0.03667 0.02826 -0.0466 0.6393 1.0000
6.000 0.7997 0.03497 0.02694 -0.0424 0.6110 1.0000
6.250 0.8352 0.03220 0.02448 -0.0370 0.5798 1.0000
6.500 0.8648 0.02917 0.02170 -0.0310 0.5379 1.0000
6.750 0.8879 0.02607 0.01872 -0.0245 0.4700 1.0000
7.000 0.8945 0.02522 0.01699 -0.0180 0.3340 1.0000
7.250 0.8906 0.02827 0.01868 -0.0141 0.2194 1.0000
7.500 0.8984 0.03160 0.02134 -0.0113 0.1545 1.0000
7.750 0.9195 0.03430 0.02365 -0.0098 0.1239 1.0000
8.000 0.9513 0.03744 0.02666 -0.0089 0.1097 1.0000
8.250 0.9761 0.04048 0.03024 -0.0076 0.1032 1.0000
8.500 0.9998 0.04396 0.03369 -0.0071 0.0964 1.0000
8.750 1.0131 0.04718 0.03762 -0.0055 0.0927 1.0000
9.000 1.0252 0.05107 0.04209 -0.0042 0.0912 1.0000
9.250 1.0324 0.05537 0.04690 -0.0029 0.0913 1.0000
9.500 1.0344 0.05992 0.05190 -0.0017 0.0920 1.0000
9.750 1.0316 0.06457 0.05693 -0.0007 0.0932 1.0000
10.000 1.0254 0.06933 0.06198 0.0001 0.0944 1.0000
10.250 1.0212 0.07433 0.06717 0.0005 0.0957 1.0000
10.500 1.0081 0.07893 0.07201 0.0009 0.0974 1.0000
10.750 0.9582 0.08347 0.07677 -0.0006 0.0991 1.0000
11.000 0.9083 0.09183 0.08515 -0.0071 0.1020 1.0000
11.250 0.8783 0.10121 0.09450 -0.0136 0.1057 1.0000
11.500 0.8734 0.10798 0.10125 -0.0161 0.1085 1.0000
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Polar data table (+)
Polar graphs
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