EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 715 AIRFOIL (e715-il) Reynolds number: 100,000 Max Cl/Cd: 44.25 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e715-il-100000-n5.txt Download as CSV file: xf-e715-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 715 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5587 0.10045 0.09580 -0.0200 1.0000 0.0202
-12.500 -0.5866 0.08930 0.08460 -0.0270 1.0000 0.0199
-12.250 -0.6087 0.08052 0.07575 -0.0330 1.0000 0.0195
-12.000 -0.6313 0.07249 0.06758 -0.0389 1.0000 0.0192
-11.750 -0.6521 0.06554 0.06048 -0.0441 1.0000 0.0191
-11.500 -0.6682 0.05978 0.05455 -0.0483 1.0000 0.0190
-11.250 -0.6821 0.05460 0.04920 -0.0520 1.0000 0.0191
-11.000 -0.6909 0.04996 0.04428 -0.0560 0.9029 0.0193
-10.750 -0.6964 0.04613 0.03994 -0.0587 0.8393 0.0197
-10.500 -0.7020 0.04343 0.03684 -0.0584 0.8094 0.0200
-10.250 -0.7040 0.04130 0.03442 -0.0573 0.7895 0.0208
-10.000 -0.6972 0.03973 0.03270 -0.0566 0.7738 0.0216
-9.750 -0.6881 0.03803 0.03075 -0.0559 0.7611 0.0227
-9.500 -0.6766 0.03619 0.02862 -0.0552 0.7508 0.0239
-9.250 -0.6627 0.03428 0.02633 -0.0543 0.7415 0.0253
-9.000 -0.6476 0.03263 0.02461 -0.0536 0.7328 0.0264
-8.750 -0.6313 0.03132 0.02317 -0.0529 0.7250 0.0283
-8.500 -0.6127 0.03005 0.02164 -0.0523 0.7172 0.0314
-8.250 -0.5956 0.02877 0.02030 -0.0516 0.7105 0.0339
-8.000 -0.5764 0.02761 0.01898 -0.0510 0.7042 0.0378
-7.750 -0.5575 0.02647 0.01779 -0.0504 0.6981 0.0424
-7.500 -0.5374 0.02548 0.01662 -0.0496 0.6932 0.0483
-7.250 -0.5171 0.02448 0.01559 -0.0492 0.6877 0.0558
-7.000 -0.4963 0.02351 0.01458 -0.0486 0.6825 0.0655
-6.750 -0.4750 0.02263 0.01363 -0.0480 0.6781 0.0785
-6.500 -0.4525 0.02181 0.01279 -0.0477 0.6732 0.0963
-6.250 -0.4300 0.02097 0.01203 -0.0474 0.6684 0.1205
-6.000 -0.4070 0.02023 0.01134 -0.0471 0.6644 0.1523
-5.750 -0.3840 0.01952 0.01070 -0.0468 0.6611 0.1902
-5.500 -0.3599 0.01890 0.01022 -0.0467 0.6568 0.2344
-5.250 -0.3358 0.01841 0.00987 -0.0464 0.6527 0.2828
-5.000 -0.3111 0.01813 0.00971 -0.0460 0.6491 0.3312
-4.750 -0.2855 0.01811 0.00970 -0.0454 0.6460 0.3720
-4.500 -0.2585 0.01822 0.00978 -0.0451 0.6419 0.4035
-4.250 -0.2312 0.01837 0.00983 -0.0449 0.6383 0.4280
-4.000 -0.2039 0.01854 0.00985 -0.0446 0.6351 0.4478
-3.750 -0.1766 0.01868 0.00983 -0.0443 0.6323 0.4647
-3.500 -0.1493 0.01882 0.00981 -0.0440 0.6294 0.4789
-3.250 -0.1218 0.01892 0.00983 -0.0439 0.6256 0.4915
-3.000 -0.0943 0.01899 0.00976 -0.0439 0.6222 0.5033
-2.750 -0.0669 0.01905 0.00972 -0.0437 0.6193 0.5137
-2.500 -0.0395 0.01909 0.00966 -0.0435 0.6169 0.5229
-2.250 -0.0119 0.01913 0.00952 -0.0434 0.6146 0.5330
-2.000 0.0155 0.01918 0.00959 -0.0434 0.6110 0.5407
-1.750 0.0432 0.01922 0.00954 -0.0435 0.6076 0.5491
-1.500 0.0706 0.01924 0.00953 -0.0434 0.6047 0.5559
-1.250 0.0984 0.01927 0.00945 -0.0434 0.6023 0.5638
-1.000 0.1260 0.01928 0.00941 -0.0433 0.6002 0.5700
-0.750 0.1537 0.01935 0.00942 -0.0434 0.5974 0.5774
-0.500 0.1810 0.01943 0.00955 -0.0435 0.5939 0.5831
-0.250 0.2085 0.01951 0.00961 -0.0436 0.5908 0.5893
0.000 0.2363 0.01959 0.00965 -0.0437 0.5883 0.5954
0.250 0.2640 0.01963 0.00968 -0.0437 0.5860 0.6008
0.500 0.2921 0.01969 0.00966 -0.0438 0.5839 0.6068
0.750 0.3192 0.01988 0.00991 -0.0440 0.5804 0.6123
1.000 0.3462 0.02006 0.01016 -0.0442 0.5771 0.6179
1.250 0.3738 0.02023 0.01033 -0.0443 0.5742 0.6242
1.500 0.4011 0.02032 0.01045 -0.0443 0.5716 0.6297
1.750 0.4289 0.02040 0.01052 -0.0443 0.5694 0.6360
2.000 0.4564 0.02057 0.01072 -0.0444 0.5669 0.6425
2.250 0.4822 0.02092 0.01121 -0.0445 0.5629 0.6491
2.500 0.5091 0.02117 0.01152 -0.0447 0.5594 0.6568
2.750 0.5366 0.02130 0.01172 -0.0447 0.5566 0.6642
3.000 0.5645 0.02141 0.01187 -0.0448 0.5543 0.6734
3.250 0.5921 0.02153 0.01206 -0.0447 0.5519 0.6835
3.500 0.6157 0.02203 0.01279 -0.0448 0.5468 0.6951
3.750 0.6415 0.02225 0.01316 -0.0447 0.5431 0.7098
4.000 0.6683 0.02229 0.01333 -0.0444 0.5401 0.7305
4.250 0.6956 0.02219 0.01342 -0.0440 0.5378 0.7637
4.500 0.7247 0.02250 0.01420 -0.0449 0.5322 0.8531
4.750 0.7639 0.02277 0.01461 -0.0476 0.5274 1.0000
5.000 0.7916 0.02288 0.01470 -0.0476 0.5242 1.0000
5.250 0.8194 0.02297 0.01477 -0.0475 0.5211 1.0000
5.500 0.8390 0.02377 0.01573 -0.0471 0.5139 1.0000
5.750 0.8659 0.02383 0.01582 -0.0469 0.5097 1.0000
6.000 0.8956 0.02364 0.01562 -0.0467 0.5067 1.0000
6.250 0.9129 0.02450 0.01667 -0.0460 0.4982 1.0000
6.500 0.9409 0.02435 0.01655 -0.0457 0.4937 1.0000
6.750 0.9627 0.02472 0.01705 -0.0451 0.4869 1.0000
7.000 0.9871 0.02480 0.01722 -0.0446 0.4803 1.0000
7.250 1.0132 0.02470 0.01719 -0.0441 0.4744 1.0000
7.500 1.0336 0.02501 0.01766 -0.0433 0.4658 1.0000
7.750 1.0566 0.02506 0.01782 -0.0425 0.4578 1.0000
8.000 1.0806 0.02494 0.01780 -0.0418 0.4490 1.0000
8.250 1.0975 0.02536 0.01838 -0.0406 0.4378 1.0000
8.500 1.1166 0.02555 0.01871 -0.0395 0.4264 1.0000
8.750 1.1354 0.02571 0.01898 -0.0384 0.4138 1.0000
9.000 1.1515 0.02602 0.01940 -0.0370 0.3993 1.0000
9.250 1.1647 0.02647 0.01992 -0.0354 0.3826 1.0000
9.500 1.1763 0.02696 0.02042 -0.0336 0.3639 1.0000
9.750 1.1824 0.02763 0.02107 -0.0312 0.3440 1.0000
10.000 1.1814 0.02904 0.02242 -0.0290 0.3230 1.0000
10.250 1.1814 0.03063 0.02388 -0.0274 0.3009 1.0000
10.500 1.1785 0.03274 0.02592 -0.0261 0.2796 1.0000
10.750 1.1754 0.03500 0.02805 -0.0250 0.2590 1.0000
11.000 1.1716 0.03745 0.03042 -0.0240 0.2395 1.0000
11.250 1.1682 0.03996 0.03287 -0.0232 0.2213 1.0000
11.500 1.1647 0.04256 0.03539 -0.0226 0.2040 1.0000
11.750 1.1619 0.04516 0.03793 -0.0220 0.1883 1.0000
12.000 1.1591 0.04783 0.04055 -0.0216 0.1733 1.0000
12.250 1.1568 0.05052 0.04323 -0.0212 0.1594 1.0000
12.500 1.1550 0.05323 0.04592 -0.0210 0.1464 1.0000
12.750 1.1536 0.05596 0.04864 -0.0208 0.1344 1.0000
13.000 1.1525 0.05880 0.05146 -0.0208 0.1233 1.0000
13.250 1.1511 0.06175 0.05439 -0.0209 0.1133 1.0000
13.500 1.1501 0.06477 0.05741 -0.0212 0.1038 1.0000
13.750 1.1507 0.06769 0.06037 -0.0214 0.0952 1.0000
14.000 1.1492 0.07091 0.06357 -0.0218 0.0881 1.0000
14.250 1.1496 0.07401 0.06675 -0.0222 0.0808 1.0000
14.500 1.1488 0.07729 0.07003 -0.0228 0.0749 1.0000
14.750 1.1490 0.08055 0.07340 -0.0234 0.0691 1.0000
15.000 1.1473 0.08408 0.07692 -0.0241 0.0645 1.0000
15.250 1.1479 0.08742 0.08039 -0.0249 0.0594 1.0000
15.500 1.1462 0.09110 0.08409 -0.0258 0.0559 1.0000
15.750 1.1467 0.09451 0.08759 -0.0266 0.0521 1.0000
16.000 1.1460 0.09823 0.09142 -0.0277 0.0485 1.0000
16.250 1.1440 0.10213 0.09534 -0.0290 0.0459 1.0000
16.500 1.1442 0.10576 0.09908 -0.0300 0.0431 1.0000
16.750 1.1434 0.10966 0.10311 -0.0314 0.0404 1.0000
17.000 1.1414 0.11380 0.10732 -0.0330 0.0383 1.0000
17.250 1.1402 0.11767 0.11119 -0.0345 0.0363 1.0000
17.500 1.1389 0.12191 0.11565 -0.0362 0.0344 1.0000
17.750 1.1364 0.12637 0.12025 -0.0382 0.0326 1.0000
18.000 1.1338 0.13086 0.12484 -0.0403 0.0310 1.0000
18.250 1.1323 0.13505 0.12904 -0.0424 0.0297 1.0000
18.500 1.1283 0.14002 0.13418 -0.0449 0.0284 1.0000
18.750 1.1225 0.14556 0.13992 -0.0478 0.0273 1.0000
19.000 1.1160 0.15137 0.14591 -0.0511 0.0263 1.0000
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Polar data table (+)
Polar graphs
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