EPPLER 638 AIRFOIL (e638-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 638 AIRFOIL (e638-il) Reynolds number: 50,000 Max Cl/Cd: 14.37 at α=0° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e638-il-50000.txt Download as CSV file: xf-e638-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 638 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3147 0.10511 0.09921 -0.0194 1.0000 0.1916
-8.500 -0.3013 0.10093 0.09511 -0.0186 1.0000 0.1998
-8.250 -0.3192 0.09984 0.09420 -0.0206 1.0000 0.2082
-8.000 -0.3034 0.09575 0.09019 -0.0192 1.0000 0.2218
-7.750 -0.2973 0.09252 0.08708 -0.0185 1.0000 0.2349
-7.500 -0.2967 0.08976 0.08447 -0.0178 1.0000 0.2483
-7.250 -0.2982 0.08722 0.08209 -0.0167 1.0000 0.2644
-7.000 -0.3268 0.08658 0.08175 -0.0157 1.0000 0.2706
-6.750 -0.3609 0.08678 0.08229 -0.0125 1.0000 0.2714
-6.500 -0.3910 0.08750 0.08322 -0.0059 1.0000 0.2697
-6.250 -0.3986 0.08593 0.08173 -0.0081 0.9893 0.2869
-5.250 0.0235 0.05810 0.05360 -0.0157 0.9643 0.9028
-4.750 0.0132 0.05457 0.05000 -0.0245 0.9157 0.7658
-4.500 -0.0628 0.05423 0.04974 -0.0263 0.8870 0.6368
-4.250 -0.1152 0.05263 0.04820 -0.0279 0.8632 0.5746
-4.000 -0.1335 0.04713 0.04149 -0.0549 0.8405 0.3297
-3.750 -0.0855 0.04366 0.03632 -0.0609 0.8267 0.1910
-3.500 -0.0553 0.04159 0.03347 -0.0603 0.8136 0.1603
-3.250 -0.0265 0.03988 0.03108 -0.0592 0.8013 0.1454
-3.000 0.0044 0.03776 0.02864 -0.0589 0.7906 0.1433
-2.750 0.0273 0.03661 0.02718 -0.0577 0.7778 0.1421
-2.500 0.0527 0.03554 0.02580 -0.0568 0.7658 0.1399
-2.250 0.0832 0.03449 0.02442 -0.0563 0.7554 0.1400
-2.000 0.1156 0.03375 0.02329 -0.0560 0.7455 0.1457
-1.750 0.1505 0.03287 0.02241 -0.0569 0.7341 0.1530
-1.500 0.3459 0.02633 0.01836 -0.0812 0.7209 1.0000
-1.250 0.3674 0.02678 0.01823 -0.0795 0.7126 1.0000
-1.000 0.3827 0.02770 0.01889 -0.0784 0.7021 1.0000
-0.750 0.4003 0.02845 0.01936 -0.0770 0.6936 1.0000
-0.500 0.4171 0.02927 0.01995 -0.0757 0.6851 1.0000
-0.250 0.4320 0.03031 0.02081 -0.0745 0.6772 1.0000
0.000 0.4484 0.03120 0.02152 -0.0731 0.6694 1.0000
0.250 0.4612 0.03240 0.02258 -0.0717 0.6620 1.0000
0.500 0.4743 0.03359 0.02363 -0.0702 0.6548 1.0000
0.750 0.4903 0.03464 0.02453 -0.0688 0.6488 1.0000
1.000 0.4923 0.03657 0.02643 -0.0670 0.6414 1.0000
1.250 0.5146 0.03725 0.02693 -0.0658 0.6359 1.0000
1.500 0.5049 0.03995 0.02962 -0.0633 0.6296 1.0000
1.750 0.5082 0.04182 0.03142 -0.0614 0.6242 1.0000
2.000 0.5360 0.04241 0.03185 -0.0607 0.6193 1.0000
2.250 0.5024 0.04630 0.03576 -0.0568 0.6148 1.0000
2.500 0.4848 0.04924 0.03865 -0.0537 0.6123 1.0000
2.750 0.4667 0.05193 0.04128 -0.0501 0.6108 1.0000
3.000 0.4567 0.05433 0.04362 -0.0474 0.6096 1.0000
3.250 0.4428 0.05705 0.04628 -0.0450 0.6116 1.0000
3.500 0.4389 0.05967 0.04884 -0.0438 0.6154 1.0000
3.750 0.4426 0.06224 0.05136 -0.0434 0.6209 1.0000
4.000 0.2936 0.06818 0.05763 -0.0388 0.7814 1.0000
4.250 0.3123 0.07028 0.05961 -0.0390 0.7713 1.0000
4.500 0.3434 0.07316 0.06238 -0.0408 0.7598 1.0000
4.750 0.3525 0.07434 0.06350 -0.0396 0.7459 1.0000
5.000 0.3614 0.07579 0.06488 -0.0385 0.7331 1.0000
5.250 0.3741 0.07769 0.06671 -0.0380 0.7222 1.0000
5.500 0.4081 0.08110 0.07006 -0.0402 0.7131 1.0000
5.750 0.4132 0.08215 0.07107 -0.0386 0.6994 1.0000
6.000 0.4189 0.08362 0.07251 -0.0374 0.6877 1.0000
6.250 0.4393 0.08639 0.07525 -0.0380 0.6799 1.0000
6.750 0.4608 0.08992 0.07873 -0.0368 0.6554 1.0000
7.000 0.4729 0.09222 0.08102 -0.0365 0.6464 1.0000
7.500 0.4981 0.09642 0.08523 -0.0360 0.6243 1.0000
7.750 0.5095 0.09884 0.08764 -0.0359 0.6153 1.0000
8.000 0.5321 0.10173 0.09055 -0.0365 0.6055 1.0000
8.250 0.5315 0.10316 0.09199 -0.0353 0.5941 1.0000
8.500 0.5483 0.10620 0.09507 -0.0357 0.5862 1.0000
8.750 0.5630 0.10855 0.09746 -0.0357 0.5749 1.0000
9.000 0.5621 0.11026 0.09919 -0.0349 0.5649 1.0000
9.250 0.5988 0.11509 0.10407 -0.0366 0.5575 1.0000
9.500 0.5890 0.11552 0.10453 -0.0351 0.5453 1.0000
9.750 0.5922 0.11784 0.10688 -0.0348 0.5364 1.0000
10.000 0.6203 0.12181 0.11095 -0.0357 0.5275 1.0000
10.250 0.6127 0.12292 0.11208 -0.0348 0.5165 1.0000
10.500 0.6280 0.12642 0.11564 -0.0353 0.5095 1.0000
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Polar data table (+)
Polar graphs
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