EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1214 AIRFOIL (e1214-il) Reynolds number: 100,000 Max Cl/Cd: 36.34 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1214-il-100000-n5.txt Download as CSV file: xf-e1214-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7145 0.09799 0.09093 -0.0300 1.0000 0.0526
-15.500 -0.7118 0.09504 0.08802 -0.0310 1.0000 0.0543
-15.250 -0.7122 0.09156 0.08455 -0.0324 1.0000 0.0568
-15.000 -0.7129 0.08812 0.08109 -0.0337 1.0000 0.0595
-14.750 -0.7136 0.08478 0.07778 -0.0350 1.0000 0.0619
-14.500 -0.7166 0.08110 0.07409 -0.0364 1.0000 0.0654
-14.250 -0.7211 0.07736 0.07038 -0.0378 1.0000 0.0687
-14.000 -0.7268 0.07351 0.06653 -0.0393 1.0000 0.0727
-13.750 -0.7349 0.06956 0.06260 -0.0408 1.0000 0.0764
-13.500 -0.7442 0.06553 0.05858 -0.0423 1.0000 0.0807
-13.250 -0.7552 0.06136 0.05440 -0.0438 1.0000 0.0853
-13.000 -0.7687 0.05696 0.05001 -0.0455 1.0000 0.0902
-12.750 -0.7812 0.05271 0.04572 -0.0470 1.0000 0.0950
-12.500 -0.7981 0.04805 0.04105 -0.0488 1.0000 0.0999
-12.250 -0.8128 0.04372 0.03666 -0.0504 1.0000 0.1052
-12.000 -0.8313 0.03931 0.03222 -0.0519 1.0000 0.1102
-11.750 -0.8465 0.03579 0.02864 -0.0524 1.0000 0.1164
-11.500 -0.8606 0.03307 0.02590 -0.0515 1.0000 0.1228
-11.250 -0.8719 0.03113 0.02396 -0.0493 1.0000 0.1299
-11.000 -0.8810 0.02971 0.02255 -0.0459 1.0000 0.1386
-10.750 -0.8881 0.02860 0.02147 -0.0420 1.0000 0.1476
-10.500 -0.8890 0.02764 0.02057 -0.0387 1.0000 0.1586
-10.250 -0.8862 0.02686 0.01985 -0.0356 1.0000 0.1698
-10.000 -0.8812 0.02623 0.01925 -0.0326 1.0000 0.1816
-9.750 -0.8676 0.02567 0.01873 -0.0312 0.9928 0.1954
-9.500 -0.8320 0.02517 0.01820 -0.0336 0.9585 0.2138
-9.250 -0.7927 0.02488 0.01780 -0.0364 0.9218 0.2310
-9.000 -0.7508 0.02473 0.01753 -0.0392 0.8894 0.2445
-8.500 -0.6872 0.02441 0.01681 -0.0407 0.8284 0.2635
-8.250 -0.6637 0.02421 0.01637 -0.0399 0.8026 0.2711
-8.000 -0.6388 0.02421 0.01627 -0.0390 0.7800 0.2774
-7.750 -0.6179 0.02392 0.01570 -0.0378 0.7598 0.2845
-7.500 -0.5937 0.02377 0.01545 -0.0369 0.7410 0.2897
-7.250 -0.5692 0.02367 0.01524 -0.0360 0.7238 0.2950
-7.000 -0.5467 0.02341 0.01474 -0.0350 0.7083 0.3012
-6.750 -0.5228 0.02314 0.01431 -0.0342 0.6932 0.3064
-6.500 -0.4970 0.02301 0.01413 -0.0336 0.6782 0.3109
-6.250 -0.4724 0.02281 0.01379 -0.0328 0.6650 0.3162
-6.000 -0.4493 0.02253 0.01324 -0.0319 0.6519 0.3221
-5.750 -0.4236 0.02232 0.01299 -0.0313 0.6390 0.3263
-5.250 -0.3729 0.02197 0.01244 -0.0301 0.6152 0.3359
-5.000 -0.3486 0.02174 0.01196 -0.0293 0.6049 0.3412
-4.750 -0.3226 0.02151 0.01170 -0.0288 0.5932 0.3452
-4.500 -0.2965 0.02136 0.01147 -0.0282 0.5835 0.3493
-4.250 -0.2708 0.02119 0.01122 -0.0277 0.5725 0.3541
-4.000 -0.2453 0.02101 0.01085 -0.0271 0.5635 0.3591
-3.750 -0.2195 0.02081 0.01057 -0.0266 0.5531 0.3635
-3.500 -0.1932 0.02068 0.01038 -0.0261 0.5446 0.3676
-3.250 -0.1670 0.02055 0.01023 -0.0257 0.5347 0.3724
-3.000 -0.1410 0.02042 0.00998 -0.0252 0.5263 0.3776
-2.750 -0.1148 0.02031 0.00972 -0.0247 0.5180 0.3826
-2.500 -0.0884 0.02018 0.00962 -0.0243 0.5093 0.3869
-2.250 -0.0621 0.02011 0.00946 -0.0238 0.5021 0.3921
-2.000 -0.0359 0.02003 0.00936 -0.0234 0.4933 0.3978
-1.750 -0.0096 0.01997 0.00917 -0.0229 0.4860 0.4034
-1.500 0.0169 0.01989 0.00910 -0.0225 0.4792 0.4082
-1.250 0.0431 0.01985 0.00907 -0.0221 0.4713 0.4141
-1.000 0.0694 0.01983 0.00893 -0.0216 0.4648 0.4210
-0.750 0.0957 0.01980 0.00891 -0.0212 0.4580 0.4270
-0.500 0.1218 0.01978 0.00892 -0.0207 0.4509 0.4332
-0.250 0.1482 0.01979 0.00885 -0.0203 0.4452 0.4406
0.000 0.1744 0.01980 0.00887 -0.0199 0.4391 0.4479
0.250 0.2001 0.01982 0.00894 -0.0194 0.4324 0.4558
0.500 0.2264 0.01986 0.00890 -0.0190 0.4267 0.4649
0.750 0.2524 0.01988 0.00895 -0.0185 0.4216 0.4730
1.000 0.2781 0.01996 0.00909 -0.0180 0.4154 0.4830
1.250 0.3038 0.02000 0.00917 -0.0175 0.4099 0.4933
1.500 0.3299 0.02006 0.00918 -0.0170 0.4053 0.5055
1.750 0.3552 0.02015 0.00938 -0.0165 0.3998 0.5179
2.000 0.3806 0.02026 0.00955 -0.0160 0.3943 0.5322
2.250 0.4062 0.02033 0.00967 -0.0155 0.3897 0.5482
2.500 0.4323 0.02041 0.00976 -0.0150 0.3857 0.5667
2.750 0.4569 0.02056 0.01006 -0.0144 0.3805 0.5876
3.000 0.4819 0.02068 0.01031 -0.0139 0.3754 0.6120
3.250 0.5068 0.02077 0.01049 -0.0132 0.3711 0.6401
3.500 0.5321 0.02085 0.01064 -0.0125 0.3676 0.6730
3.750 0.5557 0.02102 0.01101 -0.0116 0.3633 0.7123
4.000 0.5804 0.02118 0.01141 -0.0108 0.3586 0.7593
4.250 0.6114 0.02133 0.01173 -0.0111 0.3541 0.8146
4.500 0.6564 0.02156 0.01201 -0.0141 0.3499 0.8736
4.750 0.7064 0.02201 0.01254 -0.0184 0.3451 0.9221
5.000 0.7487 0.02248 0.01307 -0.0215 0.3402 0.9612
5.250 0.7901 0.02287 0.01343 -0.0244 0.3357 0.9891
5.500 0.8234 0.02318 0.01364 -0.0258 0.3322 1.0000
5.750 0.8422 0.02357 0.01396 -0.0244 0.3292 1.0000
6.000 0.8576 0.02408 0.01455 -0.0226 0.3255 1.0000
6.250 0.8747 0.02457 0.01506 -0.0210 0.3221 1.0000
6.500 0.8930 0.02500 0.01548 -0.0196 0.3189 1.0000
6.750 0.9130 0.02537 0.01579 -0.0184 0.3160 1.0000
7.000 0.9347 0.02572 0.01604 -0.0174 0.3135 1.0000
7.250 0.9493 0.02635 0.01675 -0.0157 0.3102 1.0000
7.500 0.9630 0.02701 0.01751 -0.0138 0.3067 1.0000
7.750 0.9789 0.02760 0.01814 -0.0122 0.3035 1.0000
8.000 0.9968 0.02813 0.01867 -0.0109 0.3008 1.0000
8.250 1.0170 0.02858 0.01908 -0.0098 0.2984 1.0000
8.500 1.0399 0.02898 0.01940 -0.0091 0.2961 1.0000
8.750 1.0485 0.02988 0.02044 -0.0069 0.2931 1.0000
9.000 1.0550 0.03085 0.02155 -0.0044 0.2898 1.0000
9.250 1.0647 0.03167 0.02245 -0.0024 0.2868 1.0000
9.500 1.0781 0.03238 0.02318 -0.0008 0.2842 1.0000
9.750 1.0948 0.03298 0.02378 0.0005 0.2820 1.0000
10.000 1.1165 0.03342 0.02417 0.0012 0.2800 1.0000
10.250 1.1225 0.03439 0.02520 0.0036 0.2777 1.0000
10.500 1.1016 0.03635 0.02737 0.0081 0.2747 1.0000
10.750 1.0845 0.03860 0.02978 0.0111 0.2717 1.0000
11.000 1.0759 0.04073 0.03201 0.0128 0.2688 1.0000
11.250 1.0827 0.04209 0.03341 0.0137 0.2664 1.0000
11.500 1.1029 0.04263 0.03393 0.0142 0.2645 1.0000
11.750 1.1355 0.04244 0.03366 0.0145 0.2629 1.0000
12.250 0.9132 0.06938 0.06123 0.0098 0.2468 1.0000
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