E474 (14.09%) (e474-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E474 (14.09%) (e474-il) Reynolds number: 50,000 Max Cl/Cd: 18.21 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e474-il-50000.txt Download as CSV file: xf-e474-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E474 (14.09%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4244 0.10580 0.09689 0.0149 1.0000 0.4536
-9.000 -0.4319 0.10403 0.09516 0.0156 1.0000 0.4656
-8.750 -0.4289 0.10217 0.09330 0.0165 1.0000 0.4805
-8.500 -0.3994 0.09812 0.08920 0.0162 1.0000 0.4935
-8.250 -0.3878 0.09524 0.08632 0.0165 1.0000 0.5056
-8.000 -0.3873 0.09308 0.08419 0.0173 1.0000 0.5184
-7.750 -0.3905 0.09154 0.08268 0.0188 1.0000 0.5331
-7.500 -0.5743 0.07149 0.06284 0.0018 1.0000 0.3625
-7.250 -0.5909 0.06663 0.05800 0.0020 1.0000 0.3600
-7.000 -0.6140 0.06138 0.05276 0.0023 1.0000 0.3583
-6.750 -0.6414 0.05603 0.04734 0.0033 1.0000 0.3577
-6.500 -0.6637 0.05119 0.04236 0.0050 1.0000 0.3585
-6.250 -0.6822 0.04681 0.03769 0.0071 1.0000 0.3613
-6.000 -0.6598 0.04571 0.03667 0.0087 1.0000 0.3676
-5.750 -0.6554 0.04331 0.03413 0.0105 1.0000 0.3732
-5.500 -0.6584 0.04026 0.03075 0.0126 1.0000 0.3780
-5.250 -0.6402 0.03888 0.02942 0.0141 1.0000 0.3837
-5.000 -0.6281 0.03724 0.02767 0.0158 1.0000 0.3909
-4.750 -0.6182 0.03535 0.02556 0.0175 1.0000 0.3976
-4.500 -0.5995 0.03422 0.02446 0.0190 1.0000 0.4042
-4.250 -0.5878 0.03258 0.02256 0.0206 1.0000 0.4118
-4.000 -0.5682 0.03159 0.02166 0.0220 1.0000 0.4193
-3.750 -0.5528 0.03036 0.02025 0.0234 1.0000 0.4282
-3.500 -0.5336 0.02938 0.01931 0.0248 1.0000 0.4358
-3.250 -0.5164 0.02836 0.01818 0.0260 1.0000 0.4453
-3.000 -0.4969 0.02755 0.01745 0.0274 1.0000 0.4544
-2.750 -0.4789 0.02668 0.01649 0.0286 1.0000 0.4652
-2.500 -0.4591 0.02599 0.01589 0.0298 1.0000 0.4754
-2.250 -0.4401 0.02532 0.01526 0.0310 1.0000 0.4868
-2.000 -0.4216 0.02472 0.01466 0.0321 1.0000 0.4999
-1.750 -0.4031 0.02422 0.01423 0.0333 1.0000 0.5138
-1.500 -0.3846 0.02380 0.01396 0.0344 1.0000 0.5282
-1.250 -0.3672 0.02348 0.01377 0.0355 1.0000 0.5450
-1.000 -0.3514 0.02327 0.01369 0.0365 1.0000 0.5643
-0.750 -0.3392 0.02321 0.01382 0.0376 1.0000 0.5850
-0.500 -0.2531 0.02341 0.01452 0.0261 0.9624 0.6385
-0.250 -0.1596 0.02280 0.01465 0.0160 0.9124 0.7234
0.000 -0.0001 0.02256 0.01509 0.0000 0.8469 0.8467
0.250 0.1596 0.02280 0.01465 -0.0160 0.7233 0.9124
0.500 0.2533 0.02342 0.01452 -0.0261 0.6381 0.9626
0.750 0.3391 0.02321 0.01382 -0.0376 0.5849 1.0000
1.000 0.3513 0.02327 0.01369 -0.0365 0.5640 1.0000
1.250 0.3672 0.02348 0.01377 -0.0355 0.5451 1.0000
1.500 0.3845 0.02380 0.01396 -0.0344 0.5283 1.0000
1.750 0.4030 0.02422 0.01423 -0.0333 0.5139 1.0000
2.000 0.4215 0.02471 0.01465 -0.0321 0.5000 1.0000
2.250 0.4400 0.02531 0.01525 -0.0310 0.4867 1.0000
2.500 0.4590 0.02599 0.01589 -0.0298 0.4754 1.0000
2.750 0.4788 0.02668 0.01648 -0.0286 0.4652 1.0000
3.000 0.4968 0.02755 0.01746 -0.0274 0.4545 1.0000
3.250 0.5164 0.02836 0.01818 -0.0260 0.4454 1.0000
3.500 0.5336 0.02937 0.01931 -0.0248 0.4358 1.0000
3.750 0.5527 0.03036 0.02025 -0.0234 0.4281 1.0000
4.000 0.5681 0.03158 0.02165 -0.0220 0.4193 1.0000
4.250 0.5877 0.03258 0.02256 -0.0206 0.4118 1.0000
4.500 0.5995 0.03421 0.02446 -0.0190 0.4042 1.0000
4.750 0.6182 0.03534 0.02555 -0.0175 0.3976 1.0000
5.000 0.6281 0.03724 0.02766 -0.0158 0.3908 1.0000
5.250 0.6402 0.03888 0.02942 -0.0141 0.3838 1.0000
5.500 0.6585 0.04024 0.03073 -0.0126 0.3781 1.0000
5.750 0.6554 0.04330 0.03413 -0.0105 0.3732 1.0000
6.000 0.6599 0.04570 0.03666 -0.0087 0.3676 1.0000
6.250 0.6824 0.04679 0.03767 -0.0071 0.3614 1.0000
6.500 0.6638 0.05118 0.04234 -0.0050 0.3585 1.0000
6.750 0.6415 0.05602 0.04733 -0.0034 0.3577 1.0000
7.000 0.6140 0.06138 0.05275 -0.0023 0.3583 1.0000
7.250 0.5912 0.06660 0.05798 -0.0020 0.3599 1.0000
7.500 0.5746 0.07148 0.06283 -0.0019 0.3625 1.0000
7.750 0.3910 0.09150 0.08264 -0.0188 0.5332 1.0000
8.000 0.3873 0.09303 0.08412 -0.0174 0.5185 1.0000
8.250 0.3887 0.09524 0.08631 -0.0166 0.5055 1.0000
8.500 0.4003 0.09812 0.08919 -0.0163 0.4936 1.0000
8.750 0.4324 0.10236 0.09349 -0.0167 0.4807 1.0000
9.000 0.4325 0.10400 0.09513 -0.0157 0.4657 1.0000
9.250 0.4251 0.10577 0.09686 -0.0150 0.4538 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E474 (14.09%) (e474-il)