EPPLER 59 AIRFOIL (e59-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 59 AIRFOIL (e59-il) Reynolds number: 100,000 Max Cl/Cd: 69.92 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e59-il-100000.txt Download as CSV file: xf-e59-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 59 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.4147 0.09832 0.09381 -0.0143 1.0000 0.0629
-6.250 -0.4147 0.09590 0.09144 -0.0140 1.0000 0.0646
-6.000 -0.4136 0.09339 0.08895 -0.0146 1.0000 0.0666
-5.750 -0.4099 0.09082 0.08642 -0.0170 1.0000 0.0690
-5.500 -0.3844 0.08811 0.08370 -0.0339 1.0000 0.0715
-5.250 -0.3779 0.08329 0.07890 -0.0343 1.0000 0.0724
-5.000 -0.3802 0.08004 0.07571 -0.0279 1.0000 0.0739
-4.750 -0.3730 0.07714 0.07283 -0.0265 1.0000 0.0765
-4.500 -0.3566 0.07376 0.06943 -0.0298 1.0000 0.0810
-4.250 -0.3168 0.06812 0.06368 -0.0433 1.0000 0.0878
-4.000 -0.3111 0.06584 0.06144 -0.0399 1.0000 0.0926
-3.750 -0.2671 0.06049 0.05593 -0.0516 1.0000 0.1027
-3.500 -0.2200 0.05577 0.05099 -0.0622 1.0000 0.1157
-3.250 -0.2088 0.05331 0.04859 -0.0599 1.0000 0.1206
-3.000 -0.1477 0.04855 0.04345 -0.0732 1.0000 0.1441
-2.750 -0.1230 0.04571 0.04061 -0.0746 1.0000 0.1600
-2.500 -0.0874 0.04294 0.03771 -0.0788 1.0000 0.1882
-2.250 0.0420 0.03136 0.02437 -0.1024 1.0000 0.1021
-2.000 0.0894 0.02838 0.02074 -0.1066 1.0000 0.0978
-1.750 0.1330 0.02590 0.01770 -0.1099 1.0000 0.0954
-1.500 0.1695 0.02458 0.01590 -0.1117 1.0000 0.1023
-1.250 0.2015 0.02358 0.01472 -0.1126 1.0000 0.1066
-1.000 0.2315 0.02298 0.01391 -0.1132 1.0000 0.1158
-0.750 0.2600 0.02251 0.01342 -0.1135 1.0000 0.1256
-0.500 0.2890 0.02208 0.01305 -0.1139 1.0000 0.1378
-0.250 0.3178 0.02184 0.01293 -0.1145 1.0000 0.1651
0.000 0.3622 0.01965 0.01286 -0.1172 1.0000 0.7529
0.250 0.3718 0.01969 0.01287 -0.1140 1.0000 1.0000
0.500 0.3950 0.02020 0.01316 -0.1137 1.0000 1.0000
0.750 0.4177 0.02075 0.01355 -0.1133 1.0000 1.0000
1.000 0.4398 0.02133 0.01403 -0.1130 1.0000 1.0000
1.250 0.4615 0.02197 0.01458 -0.1127 1.0000 1.0000
1.500 0.4857 0.02268 0.01523 -0.1130 0.9984 1.0000
1.750 0.5310 0.02351 0.01601 -0.1172 0.9875 1.0000
2.000 0.5797 0.02417 0.01666 -0.1218 0.9746 1.0000
2.250 0.6292 0.02457 0.01706 -0.1262 0.9609 1.0000
2.500 0.6750 0.02480 0.01734 -0.1298 0.9479 1.0000
2.750 0.7199 0.02487 0.01752 -0.1330 0.9349 1.0000
3.000 0.7658 0.02473 0.01748 -0.1362 0.9215 1.0000
3.250 0.8187 0.02388 0.01678 -0.1397 0.9035 1.0000
3.500 0.8732 0.02246 0.01558 -0.1428 0.8830 1.0000
3.750 0.9182 0.02156 0.01490 -0.1447 0.8682 1.0000
4.000 0.9640 0.02000 0.01358 -0.1458 0.8469 1.0000
4.250 1.0108 0.01775 0.01159 -0.1458 0.8121 1.0000
4.500 1.0796 0.01544 0.00920 -0.1494 0.6947 1.0000
4.750 1.1129 0.01718 0.00911 -0.1484 0.3785 1.0000
5.000 1.1130 0.02073 0.01073 -0.1438 0.1352 1.0000
5.250 1.1294 0.02235 0.01215 -0.1415 0.1081 1.0000
5.500 1.1468 0.02377 0.01352 -0.1395 0.0959 1.0000
5.750 1.1648 0.02545 0.01512 -0.1376 0.0892 1.0000
6.000 1.1889 0.02706 0.01682 -0.1365 0.0837 1.0000
6.250 1.2161 0.02923 0.01882 -0.1365 0.0759 1.0000
6.500 1.2491 0.03152 0.02134 -0.1367 0.0722 1.0000
6.750 1.2769 0.03346 0.02345 -0.1363 0.0662 1.0000
7.000 1.3112 0.03741 0.02743 -0.1373 0.0626 1.0000
7.250 1.3364 0.04073 0.03124 -0.1361 0.0613 1.0000
7.500 1.3549 0.04311 0.03424 -0.1336 0.0586 1.0000
7.750 1.3732 0.04706 0.03874 -0.1313 0.0586 1.0000
8.000 1.3882 0.05197 0.04419 -0.1289 0.0601 1.0000
8.250 1.3963 0.05710 0.05027 -0.1242 0.0668 1.0000
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Polar data table (+)
Polar graphs
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