E71 (5.15%) (e71-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: E71 (5.15%) (e71-il) Reynolds number: 500,000 Max Cl/Cd: 162.29 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e71-il-500000.txt Download as CSV file: xf-e71-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E71 (5.15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3892 0.10571 0.10357 -0.0184 1.0000 0.0090
-7.750 -0.3912 0.10350 0.10138 -0.0174 1.0000 0.0090
-7.500 -0.3949 0.10148 0.09939 -0.0161 1.0000 0.0090
-7.000 -0.3902 0.09307 0.09104 -0.0189 0.9969 0.0095
-6.750 -0.3722 0.08930 0.08726 -0.0228 0.9946 0.0097
-6.500 -0.3551 0.08564 0.08360 -0.0263 0.9912 0.0101
-6.250 -0.3332 0.08160 0.07956 -0.0318 0.9875 0.0107
-6.000 -0.3059 0.07716 0.07511 -0.0391 0.9848 0.0112
-5.750 -0.2738 0.07239 0.07032 -0.0481 0.9830 0.0127
-5.500 -0.2453 0.06795 0.06584 -0.0563 0.9763 0.0146
-5.250 -0.2014 0.06315 0.06100 -0.0675 0.9736 0.0153
-5.000 -0.1566 0.05745 0.05523 -0.0790 0.9719 0.0155
-2.500 0.2834 0.01415 0.00898 -0.1455 0.9605 0.0266
-2.250 0.3218 0.01262 0.00728 -0.1476 0.9600 0.0228
-2.000 0.3604 0.01150 0.00600 -0.1497 0.9594 0.0221
-1.750 0.3995 0.01077 0.00519 -0.1520 0.9585 0.0232
-1.500 0.4316 0.01032 0.00469 -0.1529 0.9546 0.0245
-1.250 0.4655 0.00991 0.00425 -0.1541 0.9508 0.0257
-1.000 0.5031 0.00952 0.00375 -0.1559 0.9484 0.0271
-0.750 0.5417 0.00916 0.00342 -0.1581 0.9467 0.0389
-0.500 0.5830 0.00837 0.00324 -0.1613 0.9456 0.2593
-0.250 0.6144 0.00774 0.00323 -0.1624 0.9399 0.4895
0.000 0.6430 0.00669 0.00323 -0.1622 0.9365 0.8787
0.250 0.6777 0.00629 0.00287 -0.1632 0.9333 1.0000
0.500 0.7082 0.00614 0.00269 -0.1636 0.9258 1.0000
0.750 0.7454 0.00592 0.00244 -0.1653 0.9200 1.0000
1.000 0.7770 0.00581 0.00232 -0.1659 0.9102 1.0000
1.250 0.8114 0.00570 0.00219 -0.1671 0.9000 1.0000
1.500 0.8455 0.00562 0.00208 -0.1682 0.8862 1.0000
1.750 0.8781 0.00560 0.00202 -0.1690 0.8688 1.0000
2.000 0.9082 0.00566 0.00204 -0.1692 0.8474 1.0000
2.250 0.9364 0.00577 0.00207 -0.1690 0.8208 1.0000
2.500 0.9627 0.00596 0.00214 -0.1684 0.7880 1.0000
2.750 0.9873 0.00622 0.00226 -0.1675 0.7490 1.0000
3.000 1.0094 0.00662 0.00242 -0.1660 0.6933 1.0000
3.250 1.0247 0.00749 0.00274 -0.1632 0.5798 1.0000
3.500 1.0401 0.00856 0.00317 -0.1608 0.4543 1.0000
3.750 1.0601 0.00941 0.00359 -0.1594 0.3640 1.0000
4.000 1.0788 0.01052 0.00410 -0.1580 0.2512 1.0000
4.250 1.0980 0.01167 0.00467 -0.1567 0.1463 1.0000
4.500 1.1173 0.01291 0.00536 -0.1554 0.0550 1.0000
4.750 1.1380 0.01406 0.00624 -0.1539 0.0113 1.0000
5.000 1.1621 0.01469 0.00704 -0.1530 0.0098 1.0000
5.250 1.1854 0.01542 0.00790 -0.1519 0.0093 1.0000
5.500 1.2077 0.01633 0.00894 -0.1506 0.0091 1.0000
5.750 1.2287 0.01744 0.01018 -0.1491 0.0090 1.0000
6.000 1.2486 0.01879 0.01169 -0.1474 0.0091 1.0000
6.250 1.2681 0.02047 0.01353 -0.1455 0.0094 1.0000
6.500 1.2887 0.02243 0.01569 -0.1439 0.0095 1.0000
6.750 1.3112 0.02372 0.01711 -0.1428 0.0089 1.0000
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Polar data table (+)
Polar graphs
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