EPPLER 59 AIRFOIL (e59-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 59 AIRFOIL (e59-il) Reynolds number: 50,000 Max Cl/Cd: 46.21 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e59-il-50000-n5.txt Download as CSV file: xf-e59-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.3922 0.10600 0.09959 -0.0185 1.0000 0.0774
-6.500 -0.3931 0.10375 0.09740 -0.0179 1.0000 0.0792
-6.250 -0.3936 0.10142 0.09514 -0.0180 1.0000 0.0813
-6.000 -0.3933 0.09925 0.09304 -0.0197 1.0000 0.0839
-5.750 -0.3880 0.09729 0.09115 -0.0261 1.0000 0.0857
-5.500 -0.3786 0.09386 0.08778 -0.0302 1.0000 0.0866
-5.250 -0.3790 0.09004 0.08400 -0.0228 1.0000 0.0900
-5.000 -0.3706 0.08716 0.08114 -0.0241 1.0000 0.0958
-4.750 -0.3471 0.08340 0.07737 -0.0352 1.0000 0.1011
-4.500 -0.3448 0.08020 0.07421 -0.0307 1.0000 0.1044
-4.250 -0.3286 0.07678 0.07078 -0.0335 1.0000 0.1093
-3.750 -0.2347 0.06221 0.05570 -0.0584 1.0000 0.0559
-3.500 -0.2011 0.05745 0.05078 -0.0643 1.0000 0.0540
-3.250 -0.1394 0.05088 0.04376 -0.0776 1.0000 0.0558
-3.000 -0.0760 0.04463 0.03691 -0.0896 1.0000 0.0561
-2.750 -0.0065 0.03868 0.03003 -0.1015 1.0000 0.0579
-2.500 0.0262 0.03673 0.02796 -0.1043 1.0000 0.0654
-2.250 0.0824 0.03305 0.02330 -0.1112 1.0000 0.0693
-2.000 0.1186 0.03147 0.02134 -0.1138 1.0000 0.0799
-1.750 0.1581 0.02971 0.01886 -0.1163 1.0000 0.0853
-1.500 0.1904 0.02857 0.01748 -0.1175 1.0000 0.0908
-1.250 0.2204 0.02794 0.01653 -0.1182 1.0000 0.1020
-0.750 0.2767 0.02718 0.01543 -0.1188 1.0000 0.1251
-0.500 0.3052 0.02694 0.01505 -0.1192 1.0000 0.1407
-0.250 0.3406 0.02675 0.01493 -0.1213 0.9973 0.1869
0.000 0.3846 0.02585 0.01511 -0.1253 0.9951 0.4271
0.250 0.4051 0.02496 0.01515 -0.1235 0.9871 1.0000
0.500 0.4397 0.02550 0.01533 -0.1252 0.9806 1.0000
0.750 0.4733 0.02602 0.01559 -0.1269 0.9739 1.0000
1.000 0.5096 0.02659 0.01594 -0.1290 0.9680 1.0000
1.250 0.5413 0.02705 0.01628 -0.1303 0.9600 1.0000
1.500 0.5740 0.02753 0.01666 -0.1317 0.9525 1.0000
1.750 0.6090 0.02802 0.01710 -0.1335 0.9453 1.0000
2.000 0.6391 0.02845 0.01751 -0.1345 0.9361 1.0000
2.250 0.6765 0.02890 0.01796 -0.1366 0.9294 1.0000
2.500 0.7055 0.02928 0.01841 -0.1373 0.9188 1.0000
2.750 0.7367 0.02964 0.01884 -0.1383 0.9085 1.0000
3.000 0.7717 0.02982 0.01913 -0.1397 0.8967 1.0000
3.250 0.8070 0.02982 0.01929 -0.1409 0.8822 1.0000
3.500 0.8434 0.02961 0.01925 -0.1419 0.8658 1.0000
3.750 0.8815 0.02922 0.01906 -0.1430 0.8493 1.0000
4.000 0.9186 0.02882 0.01894 -0.1439 0.8336 1.0000
4.250 0.9460 0.02875 0.01911 -0.1433 0.8151 1.0000
4.500 0.9800 0.02816 0.01881 -0.1431 0.7948 1.0000
4.750 1.0137 0.02707 0.01806 -0.1420 0.7650 1.0000
5.000 1.0449 0.02610 0.01733 -0.1403 0.7227 1.0000
5.250 1.0811 0.02502 0.01638 -0.1391 0.6546 1.0000
5.500 1.1344 0.02455 0.01492 -0.1398 0.4744 1.0000
5.750 1.1446 0.02613 0.01582 -0.1364 0.3415 1.0000
6.000 1.1539 0.02813 0.01722 -0.1336 0.2445 1.0000
6.250 1.1658 0.03041 0.01889 -0.1314 0.1454 1.0000
6.500 1.1815 0.03250 0.02071 -0.1296 0.1132 1.0000
6.750 1.1996 0.03433 0.02255 -0.1282 0.0969 1.0000
7.000 1.2193 0.03619 0.02456 -0.1269 0.0853 1.0000
7.250 1.2435 0.03813 0.02673 -0.1260 0.0779 1.0000
7.500 1.2712 0.04032 0.02913 -0.1258 0.0680 1.0000
7.750 1.3006 0.04298 0.03184 -0.1259 0.0597 1.0000
8.000 1.3277 0.04547 0.03471 -0.1255 0.0520 1.0000
8.250 1.3558 0.04900 0.03848 -0.1254 0.0467 1.0000
8.500 1.3772 0.05232 0.04230 -0.1242 0.0423 1.0000
8.750 1.3947 0.05604 0.04648 -0.1228 0.0398 1.0000
9.000 1.4057 0.06041 0.05114 -0.1211 0.0375 1.0000
9.250 1.4072 0.06422 0.05568 -0.1174 0.0359 1.0000
9.500 1.4047 0.06836 0.06039 -0.1138 0.0348 1.0000
9.750 1.3977 0.07265 0.06516 -0.1101 0.0344 1.0000
10.000 1.3850 0.07671 0.06962 -0.1061 0.0342 1.0000
10.250 1.3687 0.08082 0.07408 -0.1024 0.0341 1.0000
10.500 1.3503 0.08519 0.07877 -0.0993 0.0341 1.0000
10.750 1.3304 0.08990 0.08377 -0.0972 0.0342 1.0000
11.000 1.3092 0.09507 0.08920 -0.0962 0.0343 1.0000
11.250 1.2873 0.10080 0.09516 -0.0965 0.0345 1.0000
11.500 1.2654 0.10720 0.10175 -0.0983 0.0348 1.0000
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Polar data table (+)
Polar graphs
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