EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1214 AIRFOIL (e1214-il) Reynolds number: 200,000 Max Cl/Cd: 48.36 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1214-il-200000.txt Download as CSV file: xf-e1214-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1214 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.250 -0.9016 0.11418 0.10874 -0.0317 1.0000 0.0381
-19.000 -0.9157 0.10810 0.10249 -0.0352 1.0000 0.0381
-18.750 -0.9338 0.10155 0.09571 -0.0392 1.0000 0.0382
-18.500 -0.9420 0.09672 0.09072 -0.0418 1.0000 0.0382
-18.250 -0.9262 0.09582 0.08990 -0.0409 1.0000 0.0388
-18.000 -0.9215 0.09314 0.08719 -0.0418 1.0000 0.0392
-17.750 -0.9183 0.09025 0.08424 -0.0427 1.0000 0.0396
-17.500 -0.9157 0.08729 0.08122 -0.0438 1.0000 0.0400
-17.250 -0.9128 0.08438 0.07824 -0.0448 1.0000 0.0404
-17.000 -0.9122 0.08116 0.07493 -0.0460 1.0000 0.0412
-16.750 -0.9077 0.07859 0.07228 -0.0467 1.0000 0.0416
-16.500 -0.9094 0.07510 0.06864 -0.0481 1.0000 0.0424
-16.250 -0.9028 0.07290 0.06640 -0.0484 1.0000 0.0430
-16.000 -0.8885 0.07200 0.06563 -0.0477 1.0000 0.0441
-15.750 -0.8803 0.07014 0.06378 -0.0478 1.0000 0.0451
-15.500 -0.8750 0.06786 0.06146 -0.0482 1.0000 0.0460
-15.250 -0.8709 0.06542 0.05895 -0.0487 1.0000 0.0471
-15.000 -0.8639 0.06360 0.05715 -0.0485 1.0000 0.0483
-14.750 -0.8567 0.06184 0.05545 -0.0484 1.0000 0.0493
-14.500 -0.8539 0.05953 0.05316 -0.0487 1.0000 0.0507
-14.250 -0.8525 0.05701 0.05059 -0.0492 1.0000 0.0522
-14.000 -0.8524 0.05454 0.04815 -0.0494 1.0000 0.0538
-13.750 -0.8544 0.05177 0.04541 -0.0499 1.0000 0.0553
-13.500 -0.8581 0.04874 0.04236 -0.0505 1.0000 0.0573
-13.250 -0.8639 0.04551 0.03911 -0.0513 1.0000 0.0594
-13.000 -0.8738 0.04186 0.03546 -0.0523 1.0000 0.0618
-12.750 -0.8801 0.03857 0.03211 -0.0531 1.0000 0.0645
-12.500 -0.8935 0.03473 0.02828 -0.0541 1.0000 0.0673
-12.250 -0.9026 0.03162 0.02511 -0.0544 1.0000 0.0714
-12.000 -0.9176 0.02864 0.02214 -0.0537 1.0000 0.0757
-11.750 -0.9316 0.02640 0.01990 -0.0513 1.0000 0.0822
-11.500 -0.9451 0.02471 0.01825 -0.0475 1.0000 0.0906
-11.250 -0.9587 0.02343 0.01703 -0.0424 1.0000 0.1007
-11.000 -0.9667 0.02224 0.01592 -0.0377 1.0000 0.1158
-10.750 -0.9694 0.02115 0.01496 -0.0336 1.0000 0.1326
-10.500 -0.9660 0.02032 0.01422 -0.0302 1.0000 0.1504
-10.250 -0.9605 0.01969 0.01370 -0.0270 1.0000 0.1664
-10.000 -0.9551 0.01928 0.01336 -0.0237 1.0000 0.1806
-9.750 -0.9167 0.01886 0.01297 -0.0265 0.9894 0.2006
-9.500 -0.8708 0.01853 0.01257 -0.0303 0.9686 0.2182
-9.250 -0.8254 0.01830 0.01231 -0.0337 0.9435 0.2323
-9.000 -0.7758 0.01814 0.01209 -0.0378 0.9174 0.2444
-8.750 -0.7326 0.01803 0.01182 -0.0406 0.8844 0.2554
-8.500 -0.7025 0.01825 0.01186 -0.0406 0.8511 0.2657
-8.250 -0.6783 0.01847 0.01199 -0.0395 0.8224 0.2742
-8.000 -0.6559 0.01877 0.01212 -0.0381 0.7983 0.2829
-7.750 -0.6329 0.01883 0.01205 -0.0368 0.7772 0.2899
-7.500 -0.6081 0.01902 0.01219 -0.0358 0.7575 0.2964
-7.250 -0.5862 0.01908 0.01200 -0.0345 0.7394 0.3032
-7.000 -0.5606 0.01890 0.01180 -0.0338 0.7228 0.3084
-6.750 -0.5347 0.01892 0.01175 -0.0330 0.7074 0.3136
-6.500 -0.5105 0.01886 0.01150 -0.0321 0.6930 0.3192
-6.250 -0.4865 0.01865 0.01112 -0.0312 0.6784 0.3243
-6.000 -0.4595 0.01848 0.01095 -0.0308 0.6652 0.3287
-5.750 -0.4333 0.01841 0.01079 -0.0301 0.6521 0.3335
-5.500 -0.4081 0.01830 0.01054 -0.0294 0.6395 0.3388
-5.250 -0.3831 0.01814 0.01015 -0.0287 0.6284 0.3435
-5.000 -0.3559 0.01788 0.00995 -0.0284 0.6159 0.3478
-4.750 -0.3292 0.01781 0.00978 -0.0279 0.6054 0.3524
-4.500 -0.3031 0.01768 0.00957 -0.0273 0.5938 0.3575
-4.250 -0.2774 0.01766 0.00931 -0.0267 0.5844 0.3621
-4.000 -0.2502 0.01730 0.00901 -0.0264 0.5734 0.3665
-3.750 -0.2231 0.01722 0.00883 -0.0260 0.5642 0.3708
-3.500 -0.1964 0.01708 0.00867 -0.0256 0.5536 0.3757
-3.250 -0.1699 0.01705 0.00844 -0.0251 0.5450 0.3807
-3.000 -0.1429 0.01681 0.00820 -0.0248 0.5357 0.3851
-2.750 -0.1156 0.01667 0.00803 -0.0245 0.5270 0.3893
-2.500 -0.0885 0.01662 0.00793 -0.0241 0.5185 0.3944
-2.250 -0.0617 0.01655 0.00778 -0.0237 0.5096 0.4000
-2.000 -0.0345 0.01649 0.00758 -0.0234 0.5023 0.4049
-1.750 -0.0074 0.01634 0.00751 -0.0231 0.4940 0.4098
-1.500 0.0199 0.01628 0.00740 -0.0228 0.4866 0.4152
-1.250 0.0469 0.01632 0.00734 -0.0224 0.4794 0.4213
-1.000 0.0739 0.01619 0.00723 -0.0221 0.4716 0.4272
-0.750 0.1011 0.01616 0.00716 -0.0218 0.4651 0.4332
-0.500 0.1282 0.01620 0.00718 -0.0215 0.4585 0.4399
-0.250 0.1552 0.01615 0.00711 -0.0212 0.4516 0.4464
0.000 0.1823 0.01611 0.00707 -0.0208 0.4456 0.4534
0.250 0.2092 0.01618 0.00712 -0.0205 0.4394 0.4617
0.500 0.2359 0.01614 0.00713 -0.0201 0.4330 0.4698
0.750 0.2628 0.01614 0.00713 -0.0198 0.4276 0.4785
1.000 0.2901 0.01629 0.00719 -0.0196 0.4223 0.4882
1.250 0.3159 0.01623 0.00729 -0.0190 0.4164 0.4983
1.500 0.3425 0.01625 0.00731 -0.0187 0.4108 0.5105
1.750 0.3692 0.01630 0.00737 -0.0183 0.4062 0.5235
2.000 0.3952 0.01639 0.00755 -0.0179 0.4014 0.5378
2.250 0.4207 0.01642 0.00769 -0.0173 0.3962 0.5547
2.500 0.4464 0.01643 0.00777 -0.0168 0.3914 0.5749
2.750 0.4722 0.01647 0.00787 -0.0162 0.3870 0.5988
3.000 0.4965 0.01656 0.00812 -0.0154 0.3827 0.6276
3.250 0.5199 0.01656 0.00835 -0.0144 0.3781 0.6634
3.500 0.5434 0.01654 0.00853 -0.0133 0.3739 0.7083
3.750 0.5676 0.01651 0.00870 -0.0122 0.3700 0.7663
4.000 0.5977 0.01670 0.00905 -0.0122 0.3659 0.8364
4.250 0.6478 0.01691 0.00951 -0.0162 0.3603 0.9027
4.500 0.7026 0.01722 0.00983 -0.0212 0.3550 0.9414
4.750 0.7504 0.01758 0.01007 -0.0250 0.3508 0.9676
5.000 0.7995 0.01808 0.01054 -0.0293 0.3464 0.9854
5.250 0.8514 0.01836 0.01089 -0.0343 0.3411 0.9984
5.500 0.8748 0.01859 0.01107 -0.0337 0.3373 1.0000
5.750 0.8945 0.01883 0.01123 -0.0324 0.3342 1.0000
6.000 0.9162 0.01924 0.01152 -0.0314 0.3313 1.0000
6.250 0.9341 0.01967 0.01201 -0.0298 0.3283 1.0000
6.500 0.9517 0.02004 0.01246 -0.0282 0.3250 1.0000
6.750 0.9709 0.02038 0.01282 -0.0268 0.3216 1.0000
7.000 0.9920 0.02068 0.01309 -0.0256 0.3184 1.0000
7.250 1.0150 0.02099 0.01332 -0.0248 0.3156 1.0000
7.500 1.0388 0.02160 0.01383 -0.0242 0.3126 1.0000
7.750 1.0542 0.02204 0.01442 -0.0223 0.3098 1.0000
8.000 1.0712 0.02252 0.01499 -0.0206 0.3068 1.0000
8.250 1.0902 0.02296 0.01547 -0.0193 0.3038 1.0000
8.500 1.1113 0.02333 0.01584 -0.0182 0.3011 1.0000
8.750 1.1351 0.02369 0.01612 -0.0176 0.2985 1.0000
9.000 1.1612 0.02438 0.01671 -0.0175 0.2956 1.0000
9.250 1.1732 0.02494 0.01744 -0.0152 0.2932 1.0000
9.500 1.1864 0.02557 0.01821 -0.0132 0.2904 1.0000
9.750 1.2021 0.02617 0.01888 -0.0115 0.2877 1.0000
10.000 1.2211 0.02664 0.01938 -0.0104 0.2850 1.0000
10.250 1.2440 0.02700 0.01971 -0.0097 0.2826 1.0000
10.500 1.2709 0.02748 0.02009 -0.0097 0.2802 1.0000
10.750 1.2864 0.02839 0.02108 -0.0083 0.2778 1.0000
11.000 1.2921 0.02924 0.02212 -0.0055 0.2754 1.0000
11.250 1.2984 0.03007 0.02308 -0.0030 0.2726 1.0000
11.500 1.3086 0.03076 0.02384 -0.0009 0.2700 1.0000
11.750 1.3252 0.03125 0.02435 0.0004 0.2676 1.0000
12.000 1.3498 0.03162 0.02468 0.0007 0.2654 1.0000
12.250 1.3844 0.03222 0.02516 -0.0004 0.2628 1.0000
12.500 1.3714 0.03339 0.02654 0.0044 0.2608 1.0000
12.750 1.3546 0.03478 0.02812 0.0092 0.2586 1.0000
13.000 1.3412 0.03640 0.02990 0.0127 0.2561 1.0000
13.250 1.3373 0.03783 0.03142 0.0148 0.2536 1.0000
13.500 1.3497 0.03857 0.03217 0.0157 0.2513 1.0000
13.750 1.3869 0.03822 0.03173 0.0153 0.2490 1.0000
14.000 1.4146 0.03881 0.03227 0.0152 0.2465 1.0000
14.250 1.3537 0.04352 0.03732 0.0189 0.2442 1.0000
15.000 1.1658 0.06805 0.06245 0.0155 0.2325 1.0000
15.250 1.2970 0.05621 0.05040 0.0197 0.2332 1.0000
15.500 0.7030 0.14960 0.14442 -0.0200 0.1819 1.0000
15.750 0.7208 0.15034 0.14516 -0.0200 0.1794 1.0000
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