EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1214 AIRFOIL (e1214-il) Reynolds number: 50,000 Max Cl/Cd: 3.07 at α=11.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1214-il-50000.txt Download as CSV file: xf-e1214-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3243 0.13115 0.12355 -0.0042 1.0000 0.3614
-11.500 -0.2898 0.12502 0.11737 -0.0046 1.0000 0.3729
-11.250 -0.3244 0.12656 0.11899 -0.0046 1.0000 0.3822
-11.000 -0.2769 0.11959 0.11195 -0.0050 1.0000 0.3970
-10.750 -0.2803 0.11721 0.10961 -0.0053 1.0000 0.4062
-10.500 -0.2729 0.11528 0.10768 -0.0051 1.0000 0.4215
-10.250 -0.2520 0.11093 0.10333 -0.0056 1.0000 0.4312
-10.000 -0.2807 0.11218 0.10467 -0.0044 1.0000 0.4445
-9.750 -0.2317 0.10571 0.09815 -0.0057 1.0000 0.4573
-9.500 -0.2384 0.10409 0.09659 -0.0053 1.0000 0.4689
-9.250 -0.2299 0.10240 0.09492 -0.0048 1.0000 0.4854
-9.000 -0.2045 0.09817 0.09072 -0.0056 1.0000 0.4953
-8.750 -0.2227 0.09822 0.09088 -0.0040 1.0000 0.5098
-8.500 -0.1843 0.09383 0.08650 -0.0053 1.0000 0.5242
-8.250 -0.1768 0.09152 0.08428 -0.0052 1.0000 0.5364
-8.000 -0.2010 0.09265 0.08559 -0.0023 1.0000 0.5522
-7.750 -0.1550 0.08775 0.08077 -0.0047 1.0000 0.5652
-7.500 -0.2300 0.09313 0.08657 0.0045 1.0000 0.5737
-7.250 -0.1681 0.08824 0.08160 -0.0041 0.9801 0.5934
-7.000 -0.1162 0.08418 0.07742 -0.0126 0.9559 0.6157
-6.750 -0.0598 0.07999 0.07309 -0.0214 0.9354 0.6378
-6.500 -0.0063 0.07625 0.06916 -0.0294 0.9125 0.6599
-6.250 0.0544 0.07185 0.06450 -0.0369 0.8836 0.6796
-6.000 0.0966 0.06866 0.06108 -0.0409 0.8555 0.6945
-5.750 0.1149 0.06723 0.05950 -0.0411 0.8312 0.7104
-5.250 -0.0514 0.06058 0.05280 -0.0418 0.8146 0.5311
-5.000 -0.0519 0.05855 0.05068 -0.0411 0.7983 0.5287
-4.750 -0.0630 0.05676 0.04887 -0.0396 0.7833 0.5278
-4.500 -0.0798 0.05463 0.04669 -0.0380 0.7715 0.5276
-4.250 -0.1021 0.05230 0.04430 -0.0363 0.7595 0.5282
-4.000 -0.1335 0.04978 0.04166 -0.0342 0.7493 0.5304
-3.750 -0.0854 0.04991 0.04174 -0.0336 0.7352 0.5372
-3.500 -0.0912 0.04889 0.04071 -0.0318 0.7225 0.5410
-3.250 -0.0919 0.04718 0.03883 -0.0304 0.7138 0.5463
-3.000 -0.1120 0.04595 0.03749 -0.0283 0.7025 0.5512
-2.750 -0.0823 0.04536 0.03683 -0.0274 0.6928 0.5573
-2.500 -0.0813 0.04537 0.03685 -0.0255 0.6807 0.5624
-2.250 -0.0682 0.04433 0.03563 -0.0247 0.6725 0.5699
-2.000 -0.0701 0.04433 0.03557 -0.0229 0.6618 0.5756
-1.750 -0.0460 0.04419 0.03541 -0.0218 0.6526 0.5827
-1.500 -0.0410 0.04437 0.03552 -0.0203 0.6436 0.5896
-1.250 -0.0368 0.04443 0.03548 -0.0191 0.6345 0.5967
-1.000 0.0011 0.04393 0.03492 -0.0187 0.6279 0.6058
-0.750 -0.0202 0.04561 0.03666 -0.0159 0.6173 0.6112
-0.500 0.0033 0.04540 0.03635 -0.0154 0.6101 0.6208
-0.250 0.0104 0.04634 0.03731 -0.0139 0.6031 0.6285
0.000 -0.0077 0.04815 0.03912 -0.0115 0.5954 0.6351
0.250 0.0222 0.04810 0.03904 -0.0112 0.5886 0.6464
0.500 0.0259 0.04933 0.04023 -0.0099 0.5826 0.6567
0.750 -0.0088 0.05195 0.04286 -0.0067 0.5788 0.6619
1.000 -0.0187 0.05375 0.04472 -0.0046 0.5753 0.6697
1.250 -0.0086 0.05485 0.04576 -0.0040 0.5705 0.6829
1.500 0.0348 0.05495 0.04586 -0.0045 0.5634 0.7020
1.750 0.0237 0.05728 0.04826 -0.0030 0.5629 0.7128
2.000 0.0223 0.05929 0.05028 -0.0023 0.5629 0.7282
2.250 0.0255 0.06118 0.05222 -0.0018 0.5632 0.7468
2.500 0.0366 0.06303 0.05420 -0.0017 0.5650 0.7699
2.750 -0.0998 0.06955 0.06088 -0.0021 0.7086 0.7508
3.000 -0.0771 0.07068 0.06219 -0.0023 0.6956 0.7820
3.250 -0.0617 0.07183 0.06360 -0.0023 0.6859 0.8227
3.500 0.0319 0.07666 0.06894 -0.0167 0.6720 0.9269
3.750 0.0569 0.07785 0.06986 -0.0236 0.6586 1.0000
4.000 0.0971 0.08119 0.07281 -0.0273 0.6504 1.0000
4.250 0.0881 0.08124 0.07268 -0.0252 0.6382 1.0000
4.500 0.1211 0.08429 0.07550 -0.0270 0.6300 1.0000
4.750 0.1195 0.08540 0.07648 -0.0258 0.6223 1.0000
5.000 0.1371 0.08721 0.07814 -0.0259 0.6116 1.0000
5.250 0.1826 0.09239 0.08317 -0.0288 0.6066 1.0000
5.500 0.1586 0.09078 0.08148 -0.0253 0.5932 1.0000
5.750 0.1948 0.09468 0.08526 -0.0270 0.5869 1.0000
6.000 0.1829 0.09493 0.08544 -0.0251 0.5783 1.0000
6.250 0.2016 0.09712 0.08754 -0.0253 0.5695 1.0000
6.500 0.2428 0.10220 0.09253 -0.0275 0.5650 1.0000
6.750 0.2191 0.10089 0.09116 -0.0248 0.5534 1.0000
7.000 0.2474 0.10413 0.09432 -0.0257 0.5464 1.0000
7.250 0.2630 0.10738 0.09752 -0.0261 0.5424 1.0000
7.500 0.2554 0.10729 0.09739 -0.0248 0.5315 1.0000
7.750 0.2831 0.11076 0.10080 -0.0257 0.5256 1.0000
8.000 0.2884 0.11304 0.10303 -0.0255 0.5206 1.0000
8.250 0.2910 0.11390 0.10386 -0.0249 0.5100 1.0000
8.500 0.3203 0.11780 0.10772 -0.0259 0.5047 1.0000
8.750 0.3235 0.12000 0.10988 -0.0258 0.5006 1.0000
9.000 0.3227 0.12063 0.11050 -0.0253 0.4907 1.0000
9.250 0.3493 0.12429 0.11413 -0.0261 0.4850 1.0000
9.500 0.3596 0.12736 0.11717 -0.0264 0.4809 1.0000
9.750 0.3545 0.12751 0.11732 -0.0259 0.4712 1.0000
10.000 0.3768 0.13084 0.12063 -0.0265 0.4658 1.0000
10.250 0.4160 0.13758 0.12735 -0.0281 0.4628 1.0000
10.500 0.3850 0.13462 0.12438 -0.0268 0.4533 1.0000
10.750 0.4044 0.13760 0.12737 -0.0273 0.4469 1.0000
11.000 0.4377 0.14339 0.13315 -0.0284 0.4435 1.0000
11.250 0.4169 0.14210 0.13185 -0.0281 0.4367 1.0000
11.500 0.4298 0.14440 0.13416 -0.0284 0.4292 1.0000
11.750 0.4590 0.14934 0.13911 -0.0292 0.4248 1.0000
12.000 0.4541 0.15049 0.14026 -0.0296 0.4207 1.0000
12.250 0.4567 0.15155 0.14132 -0.0300 0.4122 1.0000
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Polar data table (+)
Polar graphs
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