EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il) Reynolds number: 50,000 Max Cl/Cd: 20.81 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1212mod-il-50000-n5.txt Download as CSV file: xf-e1212mod-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E1212MOD 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3686 0.11498 0.10714 -0.0220 1.0000 0.1420
-10.750 -0.3737 0.11050 0.10268 -0.0243 1.0000 0.1440
-10.500 -0.3887 0.10478 0.09700 -0.0278 1.0000 0.1464
-10.250 -0.3708 0.10328 0.09552 -0.0272 1.0000 0.1486
-10.000 -0.3640 0.10039 0.09266 -0.0279 1.0000 0.1507
-9.750 -0.3631 0.09687 0.08918 -0.0292 1.0000 0.1534
-9.500 -0.3730 0.09207 0.08443 -0.0317 1.0000 0.1565
-9.250 -0.4028 0.08466 0.07711 -0.0363 1.0000 0.1600
-9.000 -0.3843 0.08376 0.07625 -0.0353 1.0000 0.1623
-8.750 -0.3783 0.08136 0.07392 -0.0356 1.0000 0.1654
-8.500 -0.3930 0.07657 0.06922 -0.0379 1.0000 0.1694
-8.250 -0.5272 0.05977 0.05252 -0.0471 1.0000 0.1747
-8.000 -0.5025 0.06075 0.05366 -0.0446 1.0000 0.1768
-7.750 -0.4783 0.05942 0.05236 -0.0464 0.9722 0.1809
-7.500 -0.5128 0.04844 0.04066 -0.0560 0.9233 0.1899
-7.250 -0.4609 0.04895 0.04126 -0.0580 0.8995 0.1939
-7.000 -0.4319 0.04711 0.03923 -0.0605 0.8742 0.1997
-6.750 -0.4296 0.04284 0.03435 -0.0623 0.8506 0.2066
-6.500 -0.3971 0.04275 0.03425 -0.0623 0.8293 0.2105
-6.250 -0.3758 0.04176 0.03306 -0.0619 0.8091 0.2152
-6.000 -0.3656 0.03953 0.03036 -0.0615 0.7907 0.2211
-5.750 -0.3456 0.03855 0.02920 -0.0607 0.7737 0.2250
-5.500 -0.3226 0.03803 0.02856 -0.0597 0.7579 0.2287
-5.250 -0.3031 0.03714 0.02747 -0.0589 0.7419 0.2333
-5.000 -0.2861 0.03575 0.02571 -0.0582 0.7273 0.2383
-4.750 -0.2641 0.03496 0.02474 -0.0574 0.7144 0.2420
-4.500 -0.2410 0.03451 0.02423 -0.0565 0.7006 0.2456
-4.250 -0.2187 0.03386 0.02342 -0.0558 0.6878 0.2501
-4.000 -0.1967 0.03296 0.02221 -0.0550 0.6767 0.2549
-3.750 -0.1741 0.03227 0.02137 -0.0544 0.6642 0.2591
-3.500 -0.1491 0.03186 0.02088 -0.0536 0.6545 0.2632
-3.250 -0.1257 0.03141 0.02034 -0.0529 0.6423 0.2681
-3.000 -0.1010 0.03075 0.01938 -0.0523 0.6336 0.2739
-2.750 -0.0766 0.03033 0.01891 -0.0518 0.6222 0.2784
-2.500 -0.0505 0.02994 0.01844 -0.0511 0.6135 0.2838
-2.250 -0.0258 0.02962 0.01799 -0.0506 0.6028 0.2908
-2.000 0.0003 0.02921 0.01742 -0.0500 0.5942 0.2975
-1.750 0.0258 0.02897 0.01718 -0.0494 0.5845 0.3039
-1.500 0.0519 0.02866 0.01671 -0.0489 0.5753 0.3126
-1.250 0.0782 0.02841 0.01643 -0.0483 0.5670 0.3208
-1.000 0.1037 0.02829 0.01626 -0.0478 0.5571 0.3310
-0.750 0.1312 0.02802 0.01589 -0.0472 0.5496 0.3414
-0.500 0.1564 0.02802 0.01590 -0.0468 0.5395 0.3533
-0.250 0.1829 0.02790 0.01576 -0.0462 0.5313 0.3656
0.000 0.2089 0.02789 0.01567 -0.0456 0.5232 0.3805
0.250 0.2335 0.02794 0.01577 -0.0450 0.5138 0.3955
0.500 0.2605 0.02784 0.01561 -0.0443 0.5068 0.4117
0.750 0.2840 0.02803 0.01589 -0.0437 0.4978 0.4290
1.000 0.3089 0.02808 0.01596 -0.0430 0.4897 0.4483
1.250 0.3360 0.02798 0.01582 -0.0423 0.4837 0.4702
1.500 0.3567 0.02829 0.01637 -0.0414 0.4743 0.4928
1.750 0.3805 0.02832 0.01654 -0.0404 0.4672 0.5217
2.000 0.4062 0.02819 0.01651 -0.0394 0.4620 0.5616
2.250 0.4234 0.02855 0.01729 -0.0378 0.4532 0.6115
2.500 0.4449 0.02847 0.01765 -0.0360 0.4467 0.7025
2.750 0.5074 0.02822 0.01772 -0.0406 0.4402 0.8898
3.000 0.5538 0.02911 0.01864 -0.0451 0.4305 1.0000
3.250 0.5747 0.02954 0.01887 -0.0441 0.4251 1.0000
3.500 0.5991 0.02979 0.01887 -0.0432 0.4210 1.0000
3.750 0.6112 0.03094 0.02007 -0.0417 0.4137 1.0000
4.000 0.6297 0.03166 0.02071 -0.0405 0.4083 1.0000
4.250 0.6525 0.03212 0.02103 -0.0396 0.4043 1.0000
4.500 0.6769 0.03253 0.02126 -0.0388 0.4010 1.0000
4.750 0.6834 0.03422 0.02310 -0.0371 0.3945 1.0000
5.000 0.6994 0.03520 0.02406 -0.0359 0.3897 1.0000
5.250 0.7213 0.03575 0.02450 -0.0350 0.3860 1.0000
5.500 0.7479 0.03602 0.02464 -0.0343 0.3831 1.0000
5.750 0.7459 0.03834 0.02711 -0.0322 0.3772 1.0000
6.000 0.7505 0.04018 0.02901 -0.0306 0.3723 1.0000
6.250 0.7648 0.04136 0.03016 -0.0294 0.3688 1.0000
6.500 0.7855 0.04213 0.03087 -0.0285 0.3663 1.0000
6.750 0.8110 0.04263 0.03128 -0.0279 0.3642 1.0000
7.000 0.7039 0.05269 0.04172 -0.0233 0.3534 1.0000
7.250 0.7052 0.05520 0.04421 -0.0227 0.3495 1.0000
7.500 0.7254 0.05596 0.04492 -0.0218 0.3472 1.0000
7.750 0.7518 0.05621 0.04510 -0.0209 0.3456 1.0000
8.250 0.6415 0.07561 0.06470 -0.0263 0.3299 1.0000
8.500 0.6612 0.07670 0.06576 -0.0257 0.3280 1.0000
9.000 0.6211 0.08826 0.07740 -0.0290 0.3190 1.0000
9.250 0.6238 0.09140 0.08054 -0.0295 0.3157 1.0000
9.500 0.6357 0.09348 0.08261 -0.0295 0.3128 1.0000
9.750 0.6547 0.09481 0.08393 -0.0290 0.3105 1.0000
10.000 0.6776 0.09578 0.08489 -0.0283 0.3087 1.0000
10.250 0.6416 0.10319 0.09237 -0.0313 0.3021 1.0000
10.500 0.6467 0.10595 0.09516 -0.0317 0.2976 1.0000
10.750 0.6640 0.10739 0.09660 -0.0313 0.2941 1.0000
11.000 0.6911 0.10774 0.09692 -0.0302 0.2914 1.0000
11.250 0.6669 0.11356 0.10281 -0.0326 0.2829 1.0000
11.500 0.6802 0.11529 0.10455 -0.0325 0.2780 1.0000
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Polar data table (+)
Polar graphs
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