E471 (6.25%) (e471-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E471 (6.25%) (e471-il) Reynolds number: 500,000 Max Cl/Cd: 153.74 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e471-il-500000.txt Download as CSV file: xf-e471-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E471 (6.25%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3681 0.11494 0.11272 -0.0247 1.0000 0.0108
-9.000 -0.3697 0.11282 0.11063 -0.0242 1.0000 0.0109
-8.750 -0.3732 0.11094 0.10878 -0.0235 1.0000 0.0110
-8.500 -0.3635 0.10757 0.10542 -0.0263 0.9988 0.0111
-8.250 -0.3485 0.10353 0.10138 -0.0307 0.9968 0.0112
-8.000 -0.3326 0.09946 0.09731 -0.0352 0.9949 0.0112
-7.750 -0.3190 0.09550 0.09336 -0.0392 0.9919 0.0112
-7.500 -0.3047 0.09160 0.08946 -0.0434 0.9883 0.0112
-7.250 -0.2975 0.08604 0.08391 -0.0454 0.9862 0.0123
-7.000 -0.2788 0.08267 0.08054 -0.0497 0.9839 0.0128
-6.750 -0.2640 0.07916 0.07703 -0.0535 0.9786 0.0132
-6.500 -0.2415 0.07487 0.07274 -0.0598 0.9744 0.0138
-6.250 -0.2140 0.07029 0.06815 -0.0678 0.9719 0.0144
-6.000 -0.1838 0.06541 0.06325 -0.0767 0.9693 0.0153
-5.750 -0.1603 0.06094 0.05875 -0.0836 0.9624 0.0163
-5.500 -0.1111 0.05520 0.05294 -0.0970 0.9599 0.0180
-5.250 -0.0633 0.04876 0.04637 -0.1095 0.9584 0.0183
-5.000 -0.0244 0.03772 0.03508 -0.1233 0.9529 0.0193
-4.750 0.0051 0.03526 0.03254 -0.1271 0.9499 0.0209
-4.500 0.0453 0.03149 0.02858 -0.1331 0.9483 0.0235
-4.250 0.0940 0.02910 0.02573 -0.1379 0.9472 0.0283
-3.250 0.2601 0.01419 0.00917 -0.1550 0.9450 0.0263
-3.000 0.2983 0.01249 0.00719 -0.1571 0.9443 0.0253
-2.750 0.3233 0.01170 0.00629 -0.1564 0.9383 0.0258
-2.500 0.3584 0.01059 0.00505 -0.1578 0.9364 0.0243
-2.250 0.3940 0.00980 0.00416 -0.1594 0.9347 0.0237
-2.000 0.4300 0.00922 0.00350 -0.1610 0.9330 0.0240
-1.750 0.4661 0.00877 0.00299 -0.1627 0.9314 0.0258
-1.500 0.4930 0.00854 0.00270 -0.1623 0.9251 0.0283
-1.250 0.5269 0.00808 0.00238 -0.1636 0.9214 0.0830
-1.000 0.5622 0.00747 0.00222 -0.1655 0.9184 0.2459
-0.750 0.5906 0.00708 0.00220 -0.1658 0.9114 0.3896
-0.500 0.6231 0.00656 0.00218 -0.1669 0.9062 0.5821
-0.250 0.6494 0.00612 0.00224 -0.1665 0.8989 0.7702
0.000 0.6686 0.00566 0.00208 -0.1638 0.8916 1.0000
0.250 0.6960 0.00568 0.00204 -0.1636 0.8825 1.0000
0.500 0.7252 0.00570 0.00199 -0.1637 0.8744 1.0000
0.750 0.7536 0.00572 0.00196 -0.1637 0.8654 1.0000
1.000 0.7809 0.00577 0.00196 -0.1635 0.8552 1.0000
1.250 0.8086 0.00582 0.00197 -0.1633 0.8448 1.0000
1.500 0.8364 0.00588 0.00198 -0.1631 0.8344 1.0000
1.750 0.8637 0.00595 0.00202 -0.1629 0.8232 1.0000
2.000 0.8904 0.00602 0.00207 -0.1625 0.8103 1.0000
2.250 0.9169 0.00611 0.00213 -0.1621 0.7964 1.0000
2.500 0.9432 0.00621 0.00219 -0.1616 0.7808 1.0000
2.750 0.9689 0.00632 0.00228 -0.1610 0.7625 1.0000
3.000 0.9944 0.00647 0.00239 -0.1604 0.7416 1.0000
3.250 1.0193 0.00663 0.00251 -0.1596 0.7166 1.0000
3.500 1.0429 0.00688 0.00264 -0.1586 0.6822 1.0000
3.750 1.0635 0.00730 0.00283 -0.1570 0.6248 1.0000
4.000 1.0787 0.00814 0.00316 -0.1544 0.5246 1.0000
4.250 1.0938 0.00916 0.00367 -0.1521 0.4204 1.0000
4.500 1.1122 0.01004 0.00414 -0.1504 0.3387 1.0000
4.750 1.1290 0.01114 0.00471 -0.1487 0.2400 1.0000
5.500 1.1823 0.01452 0.00678 -0.1440 0.0223 1.0000
5.750 1.2035 0.01534 0.00760 -0.1427 0.0115 1.0000
6.000 1.2250 0.01614 0.00852 -0.1413 0.0099 1.0000
6.250 1.2441 0.01723 0.00979 -0.1396 0.0094 1.0000
6.500 1.2633 0.01826 0.01093 -0.1379 0.0092 1.0000
6.750 1.2835 0.01911 0.01187 -0.1365 0.0088 1.0000
7.000 1.3033 0.02000 0.01285 -0.1351 0.0082 1.0000
7.250 1.3211 0.02122 0.01422 -0.1333 0.0079 1.0000
7.500 1.3386 0.02261 0.01574 -0.1314 0.0077 1.0000
7.750 1.3564 0.02419 0.01746 -0.1296 0.0074 1.0000
8.000 1.3748 0.02606 0.01949 -0.1279 0.0072 1.0000
8.250 1.3942 0.02863 0.02231 -0.1263 0.0072 1.0000
8.500 1.4137 0.03286 0.02697 -0.1245 0.0079 1.0000
8.750 1.3753 0.04134 0.03726 -0.1106 0.0191 1.0000
9.000 1.3768 0.04504 0.04120 -0.1075 0.0184 1.0000
9.250 1.3749 0.04869 0.04505 -0.1041 0.0178 1.0000
9.500 1.3701 0.05229 0.04881 -0.1007 0.0173 1.0000
9.750 1.3567 0.05572 0.05240 -0.0960 0.0170 1.0000
10.000 1.3415 0.05919 0.05600 -0.0917 0.0168 1.0000
10.250 1.3186 0.06337 0.06036 -0.0874 0.0166 1.0000
10.500 1.2943 0.06798 0.06516 -0.0839 0.0166 1.0000
10.750 1.2671 0.07339 0.07077 -0.0814 0.0166 1.0000
11.000 1.2377 0.07937 0.07694 -0.0801 0.0167 1.0000
11.250 1.1983 0.08672 0.08454 -0.0804 0.0169 1.0000
11.500 1.1442 0.09630 0.09442 -0.0833 0.0174 1.0000
11.750 1.0864 0.10814 0.10653 -0.0901 0.0185 1.0000
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Polar data table (+)
Polar graphs
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