EPPLER 58 AIRFOIL (e58-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 58 AIRFOIL (e58-il) Reynolds number: 100,000 Max Cl/Cd: 70.76 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e58-il-100000.txt Download as CSV file: xf-e58-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 58 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 -0.3957 0.10947 0.10512 -0.0113 1.0000 0.0513
-6.250 -0.4001 0.10758 0.10328 -0.0096 1.0000 0.0528
-6.000 -0.4024 0.10561 0.10132 -0.0088 1.0000 0.0538
-5.750 -0.4024 0.10337 0.09912 -0.0088 1.0000 0.0555
-5.500 -0.4006 0.10115 0.09694 -0.0103 1.0000 0.0578
-5.250 -0.3914 0.09934 0.09516 -0.0169 1.0000 0.0595
-5.000 -0.3606 0.09656 0.09239 -0.0323 1.0000 0.0603
-4.750 -0.3728 0.09180 0.08768 -0.0221 1.0000 0.0615
-4.500 -0.3712 0.08880 0.08471 -0.0180 1.0000 0.0636
-4.250 -0.3602 0.08596 0.08188 -0.0193 1.0000 0.0684
-4.000 -0.3106 0.08101 0.07685 -0.0383 1.0000 0.0744
-3.750 -0.3164 0.07827 0.07418 -0.0311 1.0000 0.0767
-3.500 -0.2453 0.07306 0.06876 -0.0533 1.0000 0.0875
-3.250 -0.2504 0.07003 0.06583 -0.0468 1.0000 0.0891
-3.000 -0.1889 0.06525 0.06082 -0.0623 1.0000 0.1013
-2.750 -0.1879 0.06256 0.05822 -0.0575 1.0000 0.1040
-2.500 -0.0892 0.05820 0.05333 -0.0817 1.0000 0.1281
-2.250 -0.0889 0.05454 0.04991 -0.0770 1.0000 0.1302
-2.000 -0.0264 0.05164 0.04668 -0.0888 1.0000 0.1556
-1.750 -0.0064 0.04814 0.04328 -0.0890 1.0000 0.1600
-1.500 0.1378 0.03859 0.03237 -0.1178 1.0000 0.1148
-1.250 0.1572 0.03781 0.03181 -0.1176 1.0000 0.1334
-1.000 0.2840 0.02968 0.02152 -0.1369 1.0000 0.0889
-0.750 0.3173 0.02913 0.02079 -0.1384 1.0000 0.0958
-0.500 0.3531 0.02845 0.01970 -0.1400 1.0000 0.1007
-0.250 0.3827 0.02831 0.01958 -0.1409 1.0000 0.1116
0.000 0.4114 0.02836 0.01960 -0.1415 1.0000 0.1284
0.250 0.4479 0.02808 0.01956 -0.1435 1.0000 0.1888
0.500 0.4771 0.02828 0.01993 -0.1446 1.0000 0.2758
0.750 0.5021 0.02872 0.02055 -0.1450 1.0000 0.3413
1.000 0.5395 0.02830 0.02132 -0.1471 0.9985 0.6982
1.250 0.5782 0.02880 0.02175 -0.1496 0.9855 1.0000
1.500 0.6190 0.02956 0.02231 -0.1528 0.9743 1.0000
1.750 0.6584 0.03021 0.02283 -0.1555 0.9629 1.0000
2.000 0.6982 0.03074 0.02327 -0.1582 0.9514 1.0000
2.250 0.7385 0.03114 0.02363 -0.1609 0.9399 1.0000
2.500 0.7805 0.03137 0.02385 -0.1636 0.9284 1.0000
2.750 0.8256 0.03136 0.02385 -0.1666 0.9169 1.0000
3.000 0.8730 0.03110 0.02363 -0.1699 0.9061 1.0000
3.250 0.9140 0.03075 0.02339 -0.1718 0.8934 1.0000
3.500 0.9528 0.03036 0.02310 -0.1734 0.8809 1.0000
3.750 0.9902 0.02995 0.02281 -0.1746 0.8687 1.0000
4.000 1.0267 0.02950 0.02252 -0.1756 0.8567 1.0000
4.250 1.0654 0.02877 0.02202 -0.1766 0.8441 1.0000
4.500 1.1061 0.02768 0.02114 -0.1776 0.8305 1.0000
4.750 1.1489 0.02611 0.01982 -0.1784 0.8154 1.0000
5.000 1.1933 0.02399 0.01802 -0.1788 0.7988 1.0000
5.250 1.2223 0.02274 0.01702 -0.1770 0.7732 1.0000
5.500 1.2581 0.02115 0.01564 -0.1759 0.7329 1.0000
5.750 1.3486 0.01906 0.01242 -0.1827 0.5053 1.0000
6.000 1.3563 0.02075 0.01335 -0.1786 0.3917 1.0000
6.250 1.3551 0.02293 0.01464 -0.1734 0.2584 1.0000
6.500 1.3475 0.02718 0.01722 -0.1677 0.0808 1.0000
6.750 1.3527 0.02975 0.01971 -0.1636 0.0630 1.0000
7.000 1.3638 0.03182 0.02189 -0.1603 0.0558 1.0000
7.250 1.3800 0.03429 0.02429 -0.1583 0.0502 1.0000
7.500 1.4072 0.03646 0.02660 -0.1578 0.0446 1.0000
7.750 1.4473 0.03937 0.02968 -0.1594 0.0414 1.0000
8.000 1.4898 0.04310 0.03359 -0.1612 0.0399 1.0000
8.250 1.5246 0.04724 0.03815 -0.1615 0.0399 1.0000
8.500 1.5474 0.05131 0.04268 -0.1600 0.0397 1.0000
8.750 1.5634 0.05626 0.04797 -0.1585 0.0385 1.0000
9.000 1.5732 0.06091 0.05310 -0.1556 0.0383 1.0000
9.250 1.5720 0.06393 0.05693 -0.1499 0.0401 1.0000
9.500 1.5585 0.06988 0.06373 -0.1435 0.0436 1.0000
9.750 1.5508 0.07557 0.06983 -0.1393 0.0460 1.0000
10.000 1.5416 0.08102 0.07579 -0.1344 0.0520 1.0000
10.250 1.5036 0.08619 0.08148 -0.1273 0.0553 1.0000
10.500 1.4826 0.09187 0.08741 -0.1237 0.0583 1.0000
10.750 1.3475 0.09100 0.08679 -0.1066 0.0467 1.0000
11.000 1.3104 0.09607 0.09212 -0.1039 0.0469 1.0000
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Polar data table (+)
Polar graphs
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