EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 68 AIRFOIL (e68-il) Reynolds number: 50,000 Max Cl/Cd: 32.74 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e68-il-50000-n5.txt Download as CSV file: xf-e68-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 68 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3991 0.10647 0.09937 -0.0517 1.0000 0.0522
-10.250 -0.4106 0.10180 0.09481 -0.0525 1.0000 0.0515
-10.000 -0.4255 0.09670 0.08983 -0.0535 1.0000 0.0509
-9.750 -0.4684 0.08569 0.07897 -0.0589 1.0000 0.0488
-9.500 -0.4874 0.08125 0.07460 -0.0594 1.0000 0.0486
-9.250 -0.5116 0.07709 0.07053 -0.0596 1.0000 0.0483
-9.000 -0.5396 0.07381 0.06731 -0.0586 1.0000 0.0479
-8.750 -0.5671 0.07084 0.06438 -0.0569 1.0000 0.0476
-8.500 -0.5915 0.06723 0.06070 -0.0556 1.0000 0.0474
-8.250 -0.6112 0.06345 0.05678 -0.0544 1.0000 0.0473
-8.000 -0.6255 0.05951 0.05261 -0.0533 1.0000 0.0473
-7.750 -0.6341 0.05546 0.04822 -0.0524 1.0000 0.0475
-7.500 -0.6360 0.05155 0.04388 -0.0516 1.0000 0.0479
-7.250 -0.6284 0.04755 0.03930 -0.0517 0.9987 0.0486
-7.000 -0.6050 0.04425 0.03565 -0.0536 0.9942 0.0501
-6.750 -0.5800 0.04184 0.03298 -0.0551 0.9893 0.0524
-6.500 -0.5523 0.03963 0.03033 -0.0568 0.9847 0.0568
-6.250 -0.5258 0.03748 0.02778 -0.0578 0.9801 0.0619
-6.000 -0.4979 0.03590 0.02605 -0.0588 0.9751 0.0677
-5.750 -0.4675 0.03440 0.02435 -0.0602 0.9710 0.0771
-5.500 -0.4419 0.03316 0.02297 -0.0606 0.9653 0.0897
-5.250 -0.4119 0.03211 0.02182 -0.0619 0.9604 0.1077
-5.000 -0.3835 0.03113 0.02076 -0.0628 0.9554 0.1301
-4.750 -0.3558 0.03027 0.01984 -0.0635 0.9497 0.1560
-4.500 -0.3233 0.02951 0.01913 -0.0652 0.9452 0.1873
-4.250 -0.2982 0.02887 0.01854 -0.0654 0.9389 0.2194
-4.000 -0.2676 0.02833 0.01805 -0.0666 0.9335 0.2616
-3.750 -0.2377 0.02789 0.01773 -0.0677 0.9283 0.3085
-3.500 -0.2120 0.02755 0.01750 -0.0678 0.9217 0.3562
-3.250 -0.1792 0.02733 0.01735 -0.0690 0.9168 0.4127
-3.000 -0.1566 0.02719 0.01731 -0.0683 0.9097 0.4611
-2.750 -0.1273 0.02712 0.01731 -0.0685 0.9040 0.5141
-2.500 -0.1021 0.02711 0.01735 -0.0679 0.8977 0.5620
-2.250 -0.0776 0.02713 0.01740 -0.0670 0.8909 0.6074
-2.000 -0.0484 0.02717 0.01747 -0.0668 0.8859 0.6529
-1.750 -0.0308 0.02726 0.01758 -0.0646 0.8776 0.6917
-1.500 -0.0021 0.02731 0.01760 -0.0641 0.8725 0.7347
-1.250 0.0130 0.02741 0.01772 -0.0614 0.8640 0.7719
-1.000 0.0400 0.02743 0.01771 -0.0605 0.8585 0.8139
-0.750 0.0582 0.02752 0.01778 -0.0584 0.8503 0.8561
-0.500 0.0951 0.02754 0.01773 -0.0597 0.8450 0.9043
-0.250 0.1478 0.02763 0.01771 -0.0648 0.8399 0.9568
0.000 0.1873 0.02772 0.01761 -0.0682 0.8322 1.0000
0.250 0.2183 0.02781 0.01751 -0.0696 0.8260 1.0000
0.500 0.2403 0.02805 0.01760 -0.0695 0.8171 1.0000
0.750 0.2697 0.02824 0.01764 -0.0704 0.8102 1.0000
1.000 0.2956 0.02850 0.01778 -0.0707 0.8021 1.0000
1.250 0.3228 0.02876 0.01793 -0.0711 0.7946 1.0000
1.500 0.3511 0.02900 0.01808 -0.0716 0.7870 1.0000
1.750 0.3758 0.02933 0.01834 -0.0716 0.7786 1.0000
2.000 0.4066 0.02950 0.01845 -0.0724 0.7717 1.0000
2.250 0.4290 0.02990 0.01882 -0.0719 0.7625 1.0000
2.500 0.4624 0.02998 0.01886 -0.0729 0.7564 1.0000
2.750 0.4826 0.03046 0.01932 -0.0721 0.7463 1.0000
3.000 0.5188 0.03039 0.01926 -0.0733 0.7408 1.0000
3.500 0.5761 0.03072 0.01961 -0.0737 0.7252 1.0000
3.750 0.5929 0.03130 0.02022 -0.0724 0.7136 1.0000
4.000 0.6156 0.03167 0.02065 -0.0717 0.7036 1.0000
4.250 0.6511 0.03149 0.02052 -0.0725 0.6971 1.0000
4.500 0.6700 0.03199 0.02107 -0.0714 0.6856 1.0000
4.750 0.6987 0.03205 0.02124 -0.0713 0.6768 1.0000
5.000 0.7298 0.03197 0.02124 -0.0714 0.6680 1.0000
5.250 0.7499 0.03238 0.02174 -0.0703 0.6562 1.0000
5.500 0.7766 0.03244 0.02191 -0.0699 0.6458 1.0000
5.750 0.8142 0.03197 0.02159 -0.0705 0.6375 1.0000
6.000 0.8348 0.03225 0.02198 -0.0693 0.6245 1.0000
6.250 0.8579 0.03240 0.02225 -0.0683 0.6116 1.0000
6.750 0.9099 0.03233 0.02247 -0.0667 0.5856 1.0000
7.000 0.9361 0.03222 0.02251 -0.0658 0.5713 1.0000
7.250 0.9608 0.03216 0.02258 -0.0647 0.5556 1.0000
7.500 0.9849 0.03209 0.02268 -0.0635 0.5387 1.0000
7.750 1.0107 0.03192 0.02263 -0.0624 0.5206 1.0000
8.000 1.0320 0.03198 0.02279 -0.0609 0.5009 1.0000
8.250 1.0470 0.03237 0.02329 -0.0587 0.4790 1.0000
8.500 1.0659 0.03256 0.02357 -0.0569 0.4561 1.0000
8.750 1.0802 0.03304 0.02409 -0.0547 0.4315 1.0000
9.000 1.0914 0.03373 0.02483 -0.0523 0.4056 1.0000
9.250 1.1021 0.03451 0.02560 -0.0500 0.3789 1.0000
9.500 1.1108 0.03547 0.02652 -0.0476 0.3518 1.0000
9.750 1.1176 0.03663 0.02762 -0.0452 0.3248 1.0000
10.000 1.1219 0.03805 0.02899 -0.0428 0.2983 1.0000
10.250 1.1249 0.03969 0.03063 -0.0406 0.2727 1.0000
10.500 1.1272 0.04148 0.03236 -0.0385 0.2488 1.0000
10.750 1.1282 0.04347 0.03428 -0.0366 0.2263 1.0000
11.000 1.1293 0.04561 0.03639 -0.0349 0.2054 1.0000
11.250 1.1297 0.04790 0.03866 -0.0333 0.1860 1.0000
11.500 1.1298 0.05032 0.04103 -0.0320 0.1690 1.0000
11.750 1.1293 0.05290 0.04355 -0.0308 0.1532 1.0000
12.000 1.1294 0.05557 0.04624 -0.0298 0.1384 1.0000
12.250 1.1283 0.05844 0.04910 -0.0290 0.1249 1.0000
12.500 1.1273 0.06137 0.05205 -0.0283 0.1131 1.0000
12.750 1.1261 0.06449 0.05529 -0.0279 0.1016 1.0000
13.000 1.1255 0.06768 0.05858 -0.0276 0.0917 1.0000
13.250 1.1244 0.07097 0.06190 -0.0275 0.0836 1.0000
13.500 1.1234 0.07431 0.06531 -0.0275 0.0764 1.0000
13.750 1.1240 0.07773 0.06889 -0.0275 0.0701 1.0000
14.000 1.1234 0.08120 0.07244 -0.0277 0.0649 1.0000
14.250 1.1247 0.08467 0.07602 -0.0279 0.0606 1.0000
14.500 1.1233 0.08870 0.08032 -0.0285 0.0567 1.0000
14.750 1.1225 0.09242 0.08414 -0.0292 0.0536 1.0000
15.000 1.1245 0.09589 0.08764 -0.0296 0.0511 1.0000
15.250 1.1190 0.10107 0.09318 -0.0310 0.0496 1.0000
15.500 1.1100 0.10687 0.09929 -0.0331 0.0484 1.0000
15.750 1.0980 0.11336 0.10606 -0.0359 0.0476 1.0000
16.000 1.0825 0.12081 0.11377 -0.0397 0.0471 1.0000
16.250 1.0624 0.12974 0.12295 -0.0448 0.0470 1.0000
16.500 1.0354 0.14118 0.13461 -0.0518 0.0475 1.0000
16.750 1.0035 0.15551 0.14904 -0.0606 0.0484 1.0000
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Polar data table (+)
Polar graphs
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