E61 (5.64%) (e61-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E61 (5.64%) (e61-il) Reynolds number: 50,000 Max Cl/Cd: 45.43 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e61-il-50000-n5.txt Download as CSV file: xf-e61-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E61 (5.64%)
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 -0.3405 0.11628 0.11015 -0.0189 1.0000 0.0623
-6.500 -0.3508 0.11583 0.10980 -0.0173 1.0000 0.0632
-6.250 -0.3568 0.11518 0.10925 -0.0174 1.0000 0.0638
-6.000 -0.3599 0.11445 0.10862 -0.0192 1.0000 0.0642
-5.750 -0.3578 0.11322 0.10746 -0.0223 1.0000 0.0645
-5.500 -0.3564 0.10750 0.10180 -0.0166 1.0000 0.0660
-5.250 -0.3519 0.10412 0.09844 -0.0147 0.9994 0.0691
-5.000 -0.3308 0.10096 0.09527 -0.0203 0.9942 0.0749
-4.750 -0.2921 0.09841 0.09272 -0.0365 0.9862 0.0785
-4.500 -0.2880 0.09364 0.08797 -0.0307 0.9837 0.0825
-4.250 -0.2657 0.09035 0.08465 -0.0359 0.9780 0.0882
-4.000 -0.2227 0.08639 0.08063 -0.0497 0.9722 0.0926
-3.750 -0.2121 0.08269 0.07695 -0.0482 0.9677 0.0958
-3.500 -0.1538 0.07874 0.07284 -0.0656 0.9622 0.1058
-3.250 -0.1436 0.07485 0.06899 -0.0631 0.9585 0.1090
-3.000 -0.0931 0.07087 0.06486 -0.0757 0.9536 0.1202
-2.750 -0.0719 0.06740 0.06130 -0.0764 0.9496 0.1260
-2.500 -0.0246 0.06342 0.05719 -0.0856 0.9464 0.1386
-2.000 0.1558 0.04987 0.04245 -0.1227 0.9452 0.0635
-1.750 0.2068 0.04619 0.03853 -0.1300 0.9426 0.0586
-1.500 0.2829 0.04167 0.03320 -0.1423 0.9424 0.0532
-1.250 0.3438 0.03894 0.02953 -0.1498 0.9407 0.0507
-1.000 0.3917 0.03697 0.02702 -0.1546 0.9383 0.0504
-0.750 0.4377 0.03552 0.02496 -0.1586 0.9360 0.0506
-0.500 0.4753 0.03447 0.02357 -0.1610 0.9317 0.0517
-0.250 0.5101 0.03389 0.02276 -0.1628 0.9268 0.0588
0.000 0.5483 0.03339 0.02197 -0.1649 0.9232 0.0690
0.250 0.5797 0.03307 0.02139 -0.1657 0.9170 0.0781
0.500 0.6186 0.03259 0.02091 -0.1682 0.9125 0.1092
0.750 0.6525 0.03053 0.02092 -0.1697 0.9091 1.0000
1.000 0.6784 0.03096 0.02095 -0.1696 0.9003 1.0000
1.250 0.7122 0.03131 0.02096 -0.1709 0.8942 1.0000
1.750 0.7705 0.03208 0.02132 -0.1720 0.8783 1.0000
2.000 0.8036 0.03236 0.02146 -0.1732 0.8713 1.0000
2.250 0.8301 0.03277 0.02179 -0.1732 0.8620 1.0000
2.500 0.8678 0.03288 0.02185 -0.1750 0.8562 1.0000
2.750 0.8925 0.03329 0.02225 -0.1747 0.8457 1.0000
3.000 0.9201 0.03362 0.02258 -0.1748 0.8359 1.0000
3.250 0.9583 0.03354 0.02253 -0.1764 0.8295 1.0000
3.500 0.9839 0.03386 0.02291 -0.1760 0.8181 1.0000
3.750 1.0114 0.03408 0.02329 -0.1759 0.8070 1.0000
4.000 1.0415 0.03413 0.02345 -0.1760 0.7965 1.0000
4.250 1.0811 0.03363 0.02310 -0.1773 0.7889 1.0000
4.500 1.1093 0.03361 0.02324 -0.1768 0.7764 1.0000
4.750 1.1389 0.03345 0.02338 -0.1765 0.7636 1.0000
5.000 1.1699 0.03315 0.02331 -0.1762 0.7502 1.0000
5.250 1.2023 0.03271 0.02310 -0.1759 0.7361 1.0000
5.500 1.2368 0.03208 0.02275 -0.1758 0.7209 1.0000
5.750 1.2591 0.03208 0.02300 -0.1740 0.7001 1.0000
6.000 1.2946 0.03126 0.02261 -0.1736 0.6798 1.0000
6.250 1.3195 0.03102 0.02264 -0.1719 0.6532 1.0000
6.500 1.3429 0.03087 0.02274 -0.1699 0.6213 1.0000
6.750 1.3685 0.03062 0.02269 -0.1680 0.5815 1.0000
7.000 1.3915 0.03063 0.02278 -0.1657 0.5313 1.0000
7.250 1.4106 0.03110 0.02315 -0.1630 0.4715 1.0000
7.500 1.4218 0.03223 0.02409 -0.1595 0.4093 1.0000
7.750 1.4265 0.03389 0.02551 -0.1556 0.3490 1.0000
8.000 1.4266 0.03598 0.02733 -0.1515 0.2882 1.0000
8.250 1.4213 0.03865 0.02971 -0.1473 0.2195 1.0000
8.500 1.4148 0.04183 0.03226 -0.1437 0.1468 1.0000
8.750 1.4103 0.04542 0.03517 -0.1406 0.0814 1.0000
9.000 1.4094 0.04901 0.03856 -0.1376 0.0526 1.0000
9.250 1.4107 0.05231 0.04192 -0.1348 0.0408 1.0000
9.500 1.4123 0.05551 0.04516 -0.1325 0.0339 1.0000
9.750 1.4188 0.05830 0.04833 -0.1303 0.0290 1.0000
10.000 1.4239 0.06132 0.05159 -0.1282 0.0261 1.0000
10.250 1.4291 0.06460 0.05508 -0.1262 0.0244 1.0000
10.500 1.4392 0.06820 0.05889 -0.1243 0.0230 1.0000
10.750 1.4557 0.07155 0.06270 -0.1226 0.0221 1.0000
11.000 1.4669 0.07547 0.06709 -0.1210 0.0214 1.0000
11.250 1.4704 0.07987 0.07195 -0.1194 0.0210 1.0000
11.500 1.4674 0.08460 0.07712 -0.1180 0.0208 1.0000
11.750 1.4595 0.08965 0.08257 -0.1170 0.0207 1.0000
12.000 1.4476 0.09510 0.08840 -0.1165 0.0206 1.0000
12.250 1.4339 0.10079 0.09444 -0.1168 0.0206 1.0000
12.500 1.4185 0.10683 0.10080 -0.1179 0.0206 1.0000
12.750 1.4021 0.11330 0.10755 -0.1199 0.0207 1.0000
13.000 1.3850 0.12033 0.11484 -0.1230 0.0208 1.0000
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Polar data table (+)
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