EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1214 AIRFOIL (e1214-il) Reynolds number: 100,000 Max Cl/Cd: 25.27 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1214-il-100000.txt Download as CSV file: xf-e1214-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7651 0.10246 0.09629 -0.0377 1.0000 0.0715
-16.250 -0.8063 0.09203 0.08562 -0.0440 1.0000 0.0709
-16.000 -0.8434 0.08317 0.07648 -0.0494 1.0000 0.0708
-15.750 -0.8699 0.07638 0.06943 -0.0533 1.0000 0.0711
-15.500 -0.8909 0.07070 0.06349 -0.0563 1.0000 0.0715
-15.250 -0.8649 0.07047 0.06347 -0.0546 1.0000 0.0741
-15.000 -0.8677 0.06705 0.05997 -0.0557 1.0000 0.0759
-14.750 -0.8742 0.06321 0.05598 -0.0571 1.0000 0.0773
-14.500 -0.8858 0.05897 0.05149 -0.0588 1.0000 0.0788
-14.250 -0.8597 0.05881 0.05161 -0.0569 1.0000 0.0825
-14.000 -0.8608 0.05580 0.04849 -0.0574 1.0000 0.0854
-13.750 -0.8519 0.05397 0.04673 -0.0569 1.0000 0.0891
-13.500 -0.8504 0.05147 0.04425 -0.0570 1.0000 0.0936
-13.250 -0.8478 0.04919 0.04206 -0.0568 1.0000 0.0989
-13.000 -0.8565 0.04576 0.03854 -0.0576 1.0000 0.1047
-12.750 -0.8562 0.04352 0.03650 -0.0573 1.0000 0.1117
-12.500 -0.8645 0.04057 0.03365 -0.0573 1.0000 0.1197
-12.250 -0.8756 0.03766 0.03078 -0.0570 1.0000 0.1283
-12.000 -0.8898 0.03497 0.02813 -0.0559 1.0000 0.1383
-11.750 -0.9041 0.03288 0.02609 -0.0536 1.0000 0.1490
-11.500 -0.9160 0.03147 0.02482 -0.0500 1.0000 0.1600
-11.250 -0.9265 0.03050 0.02396 -0.0456 1.0000 0.1716
-11.000 -0.9303 0.02980 0.02333 -0.0418 1.0000 0.1853
-10.750 -0.9280 0.02944 0.02303 -0.0384 1.0000 0.1986
-10.500 -0.9218 0.02934 0.02297 -0.0352 1.0000 0.2112
-10.250 -0.9154 0.02918 0.02279 -0.0321 1.0000 0.2228
-10.000 -0.9090 0.02914 0.02270 -0.0290 1.0000 0.2340
-9.750 -0.8903 0.02993 0.02371 -0.0269 1.0000 0.2434
-9.500 -0.9013 0.02940 0.02299 -0.0219 1.0000 0.2520
-9.250 -0.8956 0.03056 0.02446 -0.0183 1.0000 0.2577
-9.000 -0.8460 0.03187 0.02584 -0.0223 0.9874 0.2730
-8.750 -0.7864 0.03292 0.02690 -0.0275 0.9703 0.2886
-8.500 -0.7246 0.03391 0.02795 -0.0324 0.9541 0.3013
-8.250 -0.6607 0.03472 0.02889 -0.0371 0.9386 0.3116
-8.000 -0.6231 0.03335 0.02718 -0.0404 0.9179 0.3243
-7.750 -0.5587 0.03441 0.02841 -0.0441 0.8978 0.3317
-7.500 -0.5501 0.03254 0.02601 -0.0433 0.8710 0.3424
-7.250 -0.5092 0.03289 0.02648 -0.0437 0.8471 0.3476
-7.000 -0.4814 0.03286 0.02635 -0.0429 0.8245 0.3542
-6.750 -0.4775 0.03131 0.02434 -0.0407 0.8049 0.3627
-6.500 -0.4470 0.03136 0.02443 -0.0400 0.7858 0.3674
-6.250 -0.4225 0.03122 0.02421 -0.0389 0.7682 0.3732
-6.000 -0.4107 0.03019 0.02279 -0.0371 0.7536 0.3809
-5.750 -0.3884 0.02965 0.02218 -0.0360 0.7374 0.3860
-5.500 -0.3629 0.02952 0.02203 -0.0351 0.7219 0.3911
-5.250 -0.3427 0.02899 0.02129 -0.0339 0.7089 0.3975
-5.000 -0.3261 0.02817 0.02017 -0.0325 0.6957 0.4040
-4.750 -0.3002 0.02790 0.01992 -0.0318 0.6822 0.4086
-4.500 -0.2753 0.02763 0.01950 -0.0309 0.6711 0.4142
-4.250 -0.2551 0.02712 0.01884 -0.0300 0.6580 0.4205
-4.000 -0.2325 0.02657 0.01804 -0.0291 0.6482 0.4258
-3.750 -0.2076 0.02631 0.01783 -0.0284 0.6353 0.4306
-3.500 -0.1825 0.02606 0.01743 -0.0277 0.6258 0.4366
-3.250 -0.1606 0.02569 0.01690 -0.0269 0.6144 0.4428
-3.000 -0.1350 0.02530 0.01634 -0.0263 0.6060 0.4478
-2.750 -0.1105 0.02514 0.01624 -0.0257 0.5943 0.4532
-2.500 -0.0846 0.02491 0.01582 -0.0251 0.5863 0.4598
-2.250 -0.0621 0.02474 0.01553 -0.0245 0.5759 0.4662
-2.000 -0.0352 0.02446 0.01524 -0.0240 0.5677 0.4713
-1.750 -0.0102 0.02442 0.01519 -0.0234 0.5588 0.4779
-1.500 0.0144 0.02429 0.01492 -0.0228 0.5500 0.4856
-1.250 0.0418 0.02411 0.01464 -0.0224 0.5433 0.4920
-1.000 0.0655 0.02414 0.01478 -0.0218 0.5339 0.4986
-0.750 0.0914 0.02404 0.01452 -0.0214 0.5269 0.5071
-0.500 0.1172 0.02403 0.01452 -0.0209 0.5198 0.5144
-0.250 0.1415 0.02408 0.01463 -0.0203 0.5114 0.5230
0.000 0.1684 0.02398 0.01440 -0.0199 0.5053 0.5324
0.250 0.1931 0.02413 0.01464 -0.0193 0.4986 0.5410
0.500 0.2169 0.02426 0.01476 -0.0187 0.4912 0.5522
0.750 0.2441 0.02418 0.01471 -0.0183 0.4855 0.5627
1.000 0.2685 0.02439 0.01491 -0.0177 0.4794 0.5754
1.250 0.2914 0.02459 0.01528 -0.0169 0.4722 0.5876
1.500 0.3176 0.02461 0.01532 -0.0164 0.4669 0.6022
1.750 0.3453 0.02470 0.01533 -0.0161 0.4625 0.6200
2.000 0.3635 0.02516 0.01606 -0.0148 0.4552 0.6385
2.250 0.3876 0.02527 0.01628 -0.0140 0.4494 0.6604
2.500 0.4148 0.02524 0.01633 -0.0134 0.4451 0.6862
2.750 0.4363 0.02567 0.01698 -0.0123 0.4401 0.7171
3.000 0.4554 0.02615 0.01778 -0.0110 0.4339 0.7559
3.250 0.4823 0.02622 0.01804 -0.0101 0.4288 0.8099
3.500 0.5299 0.02630 0.01817 -0.0126 0.4243 0.8743
3.750 0.5826 0.02768 0.01983 -0.0180 0.4164 0.9263
4.000 0.6470 0.02836 0.02046 -0.0248 0.4100 0.9648
4.250 0.7207 0.02852 0.02036 -0.0329 0.4050 0.9894
4.500 0.7402 0.02988 0.02191 -0.0341 0.3989 1.0000
4.750 0.7422 0.03082 0.02287 -0.0310 0.3945 1.0000
5.000 0.7563 0.03140 0.02337 -0.0292 0.3910 1.0000
5.250 0.7767 0.03178 0.02364 -0.0280 0.3880 1.0000
5.500 0.8021 0.03220 0.02387 -0.0274 0.3852 1.0000
5.750 0.7772 0.03519 0.02724 -0.0221 0.3794 1.0000
6.000 0.7763 0.03691 0.02903 -0.0191 0.3747 1.0000
6.250 0.7982 0.03731 0.02937 -0.0181 0.3714 1.0000
6.500 0.8271 0.03745 0.02938 -0.0178 0.3689 1.0000
6.750 0.8574 0.03784 0.02962 -0.0177 0.3666 1.0000
7.000 0.3970 0.08221 0.07494 -0.0126 0.3626 1.0000
7.250 0.5444 0.06850 0.06102 -0.0064 0.3488 1.0000
7.750 0.7157 0.05527 0.04758 -0.0012 0.3484 1.0000
8.750 0.3676 0.10811 0.10085 -0.0182 0.3760 1.0000
9.000 0.3844 0.11018 0.10289 -0.0182 0.3717 1.0000
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