EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1214 AIRFOIL (e1214-il) Reynolds number: 200,000 Max Cl/Cd: 54.02 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1214-il-200000-n5.txt Download as CSV file: xf-e1214-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7951 0.09166 0.08562 -0.0319 1.0000 0.0310
-16.000 -0.7967 0.08803 0.08197 -0.0334 1.0000 0.0316
-15.750 -0.7987 0.08438 0.07828 -0.0349 1.0000 0.0323
-15.500 -0.8004 0.08085 0.07470 -0.0363 1.0000 0.0329
-15.250 -0.8034 0.07717 0.07097 -0.0377 1.0000 0.0338
-15.000 -0.8093 0.07318 0.06695 -0.0394 1.0000 0.0346
-14.750 -0.8150 0.06929 0.06302 -0.0409 1.0000 0.0351
-14.500 -0.8232 0.06524 0.05892 -0.0425 1.0000 0.0360
-14.250 -0.8313 0.06134 0.05496 -0.0440 1.0000 0.0370
-14.000 -0.8397 0.05748 0.05103 -0.0454 1.0000 0.0382
-13.750 -0.8507 0.05335 0.04685 -0.0469 1.0000 0.0389
-13.500 -0.8618 0.04923 0.04267 -0.0484 1.0000 0.0400
-13.250 -0.8715 0.04532 0.03868 -0.0498 1.0000 0.0413
-13.000 -0.8808 0.04149 0.03477 -0.0511 1.0000 0.0431
-12.750 -0.8897 0.03780 0.03101 -0.0524 1.0000 0.0443
-12.500 -0.8975 0.03443 0.02757 -0.0533 1.0000 0.0466
-12.250 -0.9040 0.03155 0.02462 -0.0537 1.0000 0.0488
-12.000 -0.9104 0.02916 0.02218 -0.0531 1.0000 0.0520
-11.750 -0.9166 0.02725 0.02023 -0.0514 1.0000 0.0556
-11.500 -0.9209 0.02582 0.01878 -0.0488 1.0000 0.0599
-11.250 -0.9247 0.02470 0.01765 -0.0454 1.0000 0.0648
-11.000 -0.9303 0.02375 0.01672 -0.0411 1.0000 0.0705
-10.750 -0.9308 0.02287 0.01587 -0.0373 1.0000 0.0778
-10.500 -0.9133 0.02174 0.01480 -0.0370 0.9848 0.0903
-10.250 -0.8787 0.02053 0.01363 -0.0398 0.9270 0.1083
-9.750 -0.8078 0.01869 0.01170 -0.0446 0.8354 0.1480
-9.500 -0.7875 0.01821 0.01115 -0.0436 0.8028 0.1634
-9.250 -0.7681 0.01785 0.01071 -0.0422 0.7767 0.1780
-9.000 -0.7476 0.01757 0.01034 -0.0409 0.7545 0.1907
-8.500 -0.7052 0.01714 0.00976 -0.0384 0.7159 0.2171
-8.250 -0.6832 0.01701 0.00957 -0.0373 0.6990 0.2297
-8.000 -0.6602 0.01691 0.00938 -0.0363 0.6832 0.2402
-7.750 -0.6365 0.01685 0.00917 -0.0353 0.6687 0.2498
-7.500 -0.6127 0.01675 0.00901 -0.0344 0.6542 0.2568
-7.250 -0.5881 0.01668 0.00882 -0.0336 0.6409 0.2639
-6.750 -0.5381 0.01645 0.00840 -0.0322 0.6157 0.2743
-6.500 -0.5127 0.01637 0.00820 -0.0315 0.6041 0.2793
-6.250 -0.4868 0.01626 0.00795 -0.0309 0.5924 0.2844
-6.000 -0.4611 0.01614 0.00774 -0.0303 0.5818 0.2886
-5.750 -0.4352 0.01603 0.00759 -0.0297 0.5707 0.2928
-5.500 -0.4091 0.01595 0.00740 -0.0292 0.5607 0.2974
-5.250 -0.3827 0.01586 0.00719 -0.0287 0.5504 0.3020
-5.000 -0.3564 0.01576 0.00699 -0.0282 0.5413 0.3061
-4.750 -0.3300 0.01564 0.00686 -0.0277 0.5312 0.3101
-4.500 -0.3037 0.01558 0.00671 -0.0272 0.5223 0.3143
-4.250 -0.2767 0.01549 0.00654 -0.0268 0.5134 0.3185
-4.000 -0.2499 0.01544 0.00636 -0.0264 0.5049 0.3225
-3.750 -0.2232 0.01531 0.00622 -0.0260 0.4967 0.3262
-3.500 -0.1965 0.01523 0.00611 -0.0255 0.4878 0.3300
-3.250 -0.1697 0.01518 0.00598 -0.0251 0.4803 0.3338
-3.000 -0.1425 0.01512 0.00586 -0.0248 0.4723 0.3380
-2.750 -0.1155 0.01511 0.00573 -0.0244 0.4651 0.3423
-2.500 -0.0888 0.01501 0.00565 -0.0240 0.4581 0.3462
-2.250 -0.0619 0.01495 0.00558 -0.0236 0.4504 0.3502
-2.000 -0.0352 0.01494 0.00549 -0.0232 0.4436 0.3544
-1.750 -0.0078 0.01491 0.00543 -0.0229 0.4368 0.3592
-1.500 0.0192 0.01489 0.00536 -0.0226 0.4302 0.3637
-1.250 0.0455 0.01487 0.00532 -0.0221 0.4243 0.3684
-1.000 0.0726 0.01484 0.00530 -0.0218 0.4179 0.3733
-0.750 0.0996 0.01485 0.00527 -0.0214 0.4114 0.3784
-0.500 0.1263 0.01488 0.00522 -0.0210 0.4058 0.3833
-0.250 0.1530 0.01486 0.00524 -0.0206 0.4005 0.3887
0.000 0.1798 0.01486 0.00526 -0.0203 0.3947 0.3950
0.250 0.2065 0.01491 0.00525 -0.0199 0.3892 0.4013
0.500 0.2327 0.01494 0.00527 -0.0194 0.3843 0.4071
0.750 0.2595 0.01494 0.00533 -0.0191 0.3789 0.4138
1.000 0.2862 0.01499 0.00537 -0.0187 0.3739 0.4214
1.250 0.3122 0.01503 0.00541 -0.0182 0.3694 0.4291
1.500 0.3383 0.01510 0.00548 -0.0178 0.3650 0.4381
1.750 0.3649 0.01514 0.00557 -0.0174 0.3600 0.4470
2.000 0.3908 0.01518 0.00566 -0.0169 0.3553 0.4567
2.250 0.4167 0.01526 0.00573 -0.0165 0.3513 0.4676
2.500 0.4421 0.01535 0.00584 -0.0159 0.3476 0.4804
2.750 0.4680 0.01539 0.00598 -0.0155 0.3434 0.4942
3.000 0.4937 0.01546 0.00612 -0.0150 0.3391 0.5098
3.250 0.5186 0.01553 0.00624 -0.0143 0.3350 0.5268
3.500 0.5432 0.01562 0.00637 -0.0137 0.3315 0.5464
3.750 0.5681 0.01570 0.00655 -0.0130 0.3281 0.5694
4.250 0.6166 0.01580 0.00694 -0.0115 0.3208 0.6263
4.750 0.6631 0.01594 0.00731 -0.0096 0.3140 0.7011
5.000 0.6866 0.01599 0.00755 -0.0086 0.3108 0.7505
5.250 0.7142 0.01605 0.00786 -0.0083 0.3073 0.8128
5.500 0.7589 0.01625 0.00825 -0.0114 0.3034 0.8828
5.750 0.8147 0.01657 0.00860 -0.0170 0.2993 0.9345
6.000 0.8556 0.01693 0.00888 -0.0198 0.2958 0.9693
6.250 0.8944 0.01723 0.00924 -0.0221 0.2921 0.9889
6.500 0.9307 0.01754 0.00957 -0.0241 0.2885 1.0000
6.750 0.9501 0.01781 0.00984 -0.0227 0.2858 1.0000
7.000 0.9693 0.01809 0.01009 -0.0212 0.2832 1.0000
7.250 0.9885 0.01840 0.01035 -0.0198 0.2808 1.0000
7.500 1.0078 0.01874 0.01065 -0.0184 0.2784 1.0000
7.750 1.0266 0.01904 0.01102 -0.0169 0.2756 1.0000
8.000 1.0451 0.01936 0.01138 -0.0154 0.2727 1.0000
8.250 1.0632 0.01968 0.01172 -0.0139 0.2700 1.0000
8.500 1.0813 0.02002 0.01207 -0.0124 0.2675 1.0000
8.750 1.0994 0.02038 0.01241 -0.0109 0.2653 1.0000
9.000 1.1178 0.02078 0.01276 -0.0095 0.2632 1.0000
9.250 1.1349 0.02119 0.01322 -0.0079 0.2610 1.0000
9.500 1.1505 0.02160 0.01371 -0.0062 0.2585 1.0000
9.750 1.1654 0.02203 0.01420 -0.0044 0.2559 1.0000
10.000 1.1783 0.02245 0.01465 -0.0022 0.2535 1.0000
10.250 1.1908 0.02289 0.01511 -0.0001 0.2513 1.0000
10.500 1.2045 0.02336 0.01558 0.0018 0.2494 1.0000
10.750 1.2198 0.02387 0.01605 0.0034 0.2475 1.0000
11.000 1.2312 0.02447 0.01673 0.0053 0.2454 1.0000
11.250 1.2407 0.02516 0.01752 0.0072 0.2431 1.0000
11.500 1.2503 0.02589 0.01833 0.0090 0.2406 1.0000
11.750 1.2605 0.02666 0.01917 0.0105 0.2384 1.0000
12.000 1.2710 0.02747 0.02002 0.0119 0.2363 1.0000
12.250 1.2826 0.02826 0.02082 0.0130 0.2343 1.0000
12.500 1.2964 0.02902 0.02155 0.0140 0.2322 1.0000
12.750 1.3031 0.03019 0.02282 0.0152 0.2301 1.0000
13.000 1.3067 0.03161 0.02438 0.0162 0.2277 1.0000
13.250 1.3109 0.03307 0.02594 0.0171 0.2252 1.0000
13.500 1.3156 0.03456 0.02750 0.0178 0.2227 1.0000
13.750 1.3226 0.03595 0.02893 0.0183 0.2205 1.0000
14.000 1.3329 0.03710 0.03007 0.0188 0.2183 1.0000
14.250 1.3395 0.03863 0.03164 0.0192 0.2162 1.0000
14.500 1.3325 0.04137 0.03456 0.0194 0.2135 1.0000
14.750 1.3281 0.04402 0.03734 0.0193 0.2109 1.0000
15.000 1.3254 0.04658 0.03998 0.0191 0.2081 1.0000
15.250 1.3281 0.04864 0.04208 0.0191 0.2058 1.0000
15.500 1.3390 0.04988 0.04330 0.0192 0.2036 1.0000
15.750 1.3280 0.05353 0.04710 0.0185 0.2010 1.0000
16.000 1.3046 0.05880 0.05256 0.0171 0.1977 1.0000
16.250 1.2886 0.06344 0.05732 0.0157 0.1946 1.0000
16.500 1.2883 0.06623 0.06015 0.0150 0.1919 1.0000
16.750 1.3051 0.06689 0.06076 0.0151 0.1898 1.0000
17.000 1.2388 0.07854 0.07272 0.0106 0.1850 1.0000
17.250 1.1936 0.08793 0.08227 0.0069 0.1798 1.0000
17.500 1.2121 0.08838 0.08270 0.0070 0.1778 1.0000
17.750 1.2436 0.08693 0.08119 0.0079 0.1763 1.0000
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Polar data table (+)
Polar graphs
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