EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1214 AIRFOIL (e1214-il) Reynolds number: 500,000 Max Cl/Cd: 80.49 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1214-il-500000-n5.txt Download as CSV file: xf-e1214-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8980 0.08784 0.08295 -0.0325 1.0000 0.0185
-16.750 -0.9021 0.08395 0.07900 -0.0341 1.0000 0.0186
-16.500 -0.9064 0.08006 0.07505 -0.0357 1.0000 0.0189
-16.250 -0.9118 0.07609 0.07103 -0.0373 1.0000 0.0189
-16.000 -0.9168 0.07223 0.06710 -0.0388 1.0000 0.0192
-15.750 -0.9243 0.06810 0.06291 -0.0404 1.0000 0.0194
-15.500 -0.9303 0.06428 0.05902 -0.0419 1.0000 0.0195
-15.250 -0.9399 0.06019 0.05485 -0.0434 1.0000 0.0197
-15.000 -0.9493 0.05619 0.05078 -0.0449 1.0000 0.0199
-14.750 -0.9578 0.05231 0.04682 -0.0463 1.0000 0.0200
-14.500 -0.9681 0.04824 0.04267 -0.0477 1.0000 0.0202
-14.250 -0.9791 0.04406 0.03841 -0.0492 1.0000 0.0204
-14.000 -0.9886 0.04003 0.03430 -0.0508 1.0000 0.0207
-13.750 -0.9947 0.03640 0.03058 -0.0521 1.0000 0.0208
-13.500 -0.9989 0.03305 0.02713 -0.0534 1.0000 0.0211
-13.250 -1.0010 0.03012 0.02413 -0.0543 1.0000 0.0215
-13.000 -1.0023 0.02763 0.02155 -0.0545 1.0000 0.0220
-12.750 -1.0011 0.02573 0.01959 -0.0540 1.0000 0.0224
-12.500 -0.9998 0.02420 0.01799 -0.0527 1.0000 0.0230
-12.250 -0.9984 0.02296 0.01670 -0.0507 1.0000 0.0235
-12.000 -0.9978 0.02192 0.01563 -0.0478 1.0000 0.0244
-11.750 -0.9899 0.02105 0.01472 -0.0457 0.9967 0.0253
-11.500 -0.9211 0.01965 0.01326 -0.0554 0.9093 0.0288
-11.250 -0.8979 0.01903 0.01234 -0.0555 0.8253 0.0314
-11.000 -0.8924 0.01858 0.01173 -0.0520 0.7865 0.0342
-10.750 -0.8836 0.01813 0.01116 -0.0490 0.7584 0.0380
-10.500 -0.8714 0.01761 0.01056 -0.0467 0.7353 0.0433
-10.250 -0.8568 0.01711 0.00999 -0.0446 0.7150 0.0491
-10.000 -0.8413 0.01658 0.00943 -0.0428 0.6969 0.0570
-9.750 -0.8247 0.01606 0.00888 -0.0410 0.6807 0.0664
-9.500 -0.8071 0.01554 0.00836 -0.0394 0.6656 0.0778
-9.250 -0.7888 0.01502 0.00784 -0.0379 0.6510 0.0909
-9.000 -0.7689 0.01455 0.00738 -0.0367 0.6374 0.1046
-8.750 -0.7487 0.01409 0.00693 -0.0354 0.6247 0.1189
-8.500 -0.7273 0.01367 0.00653 -0.0343 0.6120 0.1335
-8.250 -0.7050 0.01330 0.00617 -0.0333 0.6001 0.1484
-8.000 -0.6821 0.01296 0.00585 -0.0324 0.5882 0.1635
-7.750 -0.6584 0.01266 0.00558 -0.0316 0.5776 0.1788
-7.500 -0.6341 0.01242 0.00534 -0.0309 0.5666 0.1936
-7.250 -0.6089 0.01222 0.00514 -0.0303 0.5566 0.2073
-7.000 -0.5831 0.01208 0.00497 -0.0297 0.5456 0.2187
-6.750 -0.5571 0.01193 0.00482 -0.0292 0.5366 0.2277
-6.500 -0.5305 0.01184 0.00468 -0.0287 0.5265 0.2369
-6.250 -0.5041 0.01173 0.00457 -0.0283 0.5173 0.2464
-6.000 -0.4768 0.01168 0.00444 -0.0279 0.5075 0.2525
-5.750 -0.4503 0.01157 0.00433 -0.0275 0.4995 0.2580
-5.500 -0.4230 0.01150 0.00421 -0.0271 0.4912 0.2627
-5.250 -0.3956 0.01147 0.00410 -0.0268 0.4826 0.2667
-5.000 -0.3680 0.01140 0.00398 -0.0264 0.4744 0.2703
-4.750 -0.3411 0.01134 0.00389 -0.0260 0.4658 0.2746
-4.500 -0.3136 0.01128 0.00380 -0.0257 0.4587 0.2787
-4.250 -0.2858 0.01125 0.00371 -0.0254 0.4513 0.2829
-4.000 -0.2580 0.01125 0.00363 -0.0252 0.4440 0.2863
-3.750 -0.2307 0.01117 0.00355 -0.0248 0.4372 0.2904
-3.500 -0.2033 0.01112 0.00348 -0.0245 0.4294 0.2941
-3.250 -0.1758 0.01111 0.00341 -0.0242 0.4225 0.2978
-3.000 -0.1477 0.01109 0.00335 -0.0240 0.4165 0.3014
-2.750 -0.1197 0.01109 0.00330 -0.0237 0.4099 0.3042
-2.500 -0.0925 0.01106 0.00324 -0.0234 0.4037 0.3077
-2.250 -0.0648 0.01102 0.00320 -0.0231 0.3976 0.3113
-2.000 -0.0371 0.01102 0.00316 -0.0229 0.3910 0.3152
-1.750 -0.0096 0.01104 0.00314 -0.0226 0.3852 0.3191
-1.500 0.0187 0.01104 0.00311 -0.0224 0.3804 0.3224
-1.250 0.0463 0.01103 0.00309 -0.0221 0.3747 0.3260
-1.000 0.0736 0.01104 0.00307 -0.0218 0.3688 0.3299
-0.750 0.1013 0.01105 0.00307 -0.0216 0.3638 0.3341
-0.500 0.1292 0.01106 0.00307 -0.0213 0.3589 0.3384
-0.250 0.1570 0.01110 0.00307 -0.0211 0.3539 0.3422
0.000 0.1840 0.01113 0.00309 -0.0208 0.3489 0.3470
0.250 0.2117 0.01113 0.00310 -0.0205 0.3447 0.3516
0.500 0.2394 0.01115 0.00313 -0.0203 0.3399 0.3564
0.750 0.2669 0.01121 0.00315 -0.0201 0.3355 0.3608
1.000 0.2939 0.01126 0.00319 -0.0197 0.3313 0.3662
1.250 0.3214 0.01127 0.00324 -0.0195 0.3277 0.3723
1.500 0.3490 0.01131 0.00328 -0.0192 0.3237 0.3784
1.750 0.3763 0.01137 0.00333 -0.0190 0.3192 0.3837
2.000 0.4030 0.01143 0.00340 -0.0186 0.3153 0.3903
2.250 0.4299 0.01149 0.00347 -0.0183 0.3119 0.3977
2.500 0.4573 0.01153 0.00354 -0.0180 0.3090 0.4053
2.750 0.4843 0.01157 0.00362 -0.0177 0.3055 0.4145
3.000 0.5112 0.01164 0.00370 -0.0174 0.3017 0.4231
3.250 0.5373 0.01172 0.00380 -0.0170 0.2979 0.4327
3.500 0.5638 0.01181 0.00390 -0.0166 0.2947 0.4433
3.750 0.5905 0.01184 0.00401 -0.0163 0.2920 0.4560
4.000 0.6170 0.01190 0.00412 -0.0159 0.2890 0.4701
4.250 0.6431 0.01197 0.00424 -0.0155 0.2859 0.4859
4.500 0.6686 0.01205 0.00437 -0.0150 0.2827 0.5023
4.750 0.6937 0.01215 0.00451 -0.0145 0.2795 0.5203
5.000 0.7194 0.01220 0.00465 -0.0140 0.2768 0.5423
5.250 0.7448 0.01224 0.00480 -0.0135 0.2740 0.5689
5.500 0.7696 0.01229 0.00496 -0.0128 0.2712 0.5980
5.750 0.7937 0.01234 0.00512 -0.0121 0.2685 0.6302
6.000 0.8170 0.01241 0.00530 -0.0112 0.2657 0.6652
6.250 0.8391 0.01249 0.00550 -0.0101 0.2630 0.7070
6.500 0.8613 0.01246 0.00569 -0.0089 0.2609 0.7615
6.750 0.8827 0.01241 0.00589 -0.0075 0.2583 0.8296
7.000 0.9263 0.01251 0.00623 -0.0105 0.2548 0.9186
7.250 0.9871 0.01285 0.00658 -0.0174 0.2511 0.9637
7.500 1.0232 0.01316 0.00686 -0.0193 0.2482 0.9822
7.750 1.0573 0.01342 0.00714 -0.0207 0.2458 0.9932
8.000 1.0942 0.01366 0.00739 -0.0227 0.2434 0.9996
8.250 1.1158 0.01387 0.00762 -0.0216 0.2410 1.0000
8.500 1.1349 0.01410 0.00785 -0.0201 0.2384 1.0000
8.750 1.1533 0.01435 0.00810 -0.0185 0.2360 1.0000
9.000 1.1707 0.01464 0.00838 -0.0167 0.2337 1.0000
9.250 1.1873 0.01495 0.00868 -0.0149 0.2316 1.0000
9.500 1.2060 0.01517 0.00894 -0.0133 0.2299 1.0000
9.750 1.2237 0.01543 0.00924 -0.0116 0.2280 1.0000
10.000 1.2389 0.01570 0.00954 -0.0095 0.2258 1.0000
10.250 1.2515 0.01600 0.00985 -0.0070 0.2236 1.0000
10.500 1.2637 0.01634 0.01020 -0.0045 0.2215 1.0000
10.750 1.2758 0.01674 0.01061 -0.0022 0.2195 1.0000
11.000 1.2873 0.01721 0.01108 0.0000 0.2175 1.0000
11.250 1.3022 0.01761 0.01153 0.0017 0.2156 1.0000
11.500 1.3172 0.01805 0.01202 0.0033 0.2137 1.0000
11.750 1.3312 0.01856 0.01257 0.0048 0.2114 1.0000
12.000 1.3440 0.01916 0.01321 0.0063 0.2091 1.0000
12.250 1.3554 0.01989 0.01395 0.0077 0.2068 1.0000
12.500 1.3653 0.02076 0.01484 0.0091 0.2045 1.0000
12.750 1.3758 0.02167 0.01579 0.0103 0.2022 1.0000
13.000 1.3894 0.02248 0.01666 0.0111 0.2003 1.0000
13.250 1.4014 0.02343 0.01767 0.0119 0.1979 1.0000
13.500 1.4118 0.02454 0.01883 0.0126 0.1955 1.0000
13.750 1.4207 0.02581 0.02013 0.0133 0.1932 1.0000
14.000 1.4273 0.02730 0.02165 0.0138 0.1909 1.0000
14.250 1.4337 0.02887 0.02325 0.0143 0.1889 1.0000
14.500 1.4441 0.03018 0.02465 0.0146 0.1870 1.0000
14.750 1.4523 0.03169 0.02623 0.0149 0.1848 1.0000
15.000 1.4580 0.03345 0.02805 0.0151 0.1822 1.0000
15.250 1.4612 0.03547 0.03011 0.0152 0.1797 1.0000
15.500 1.4614 0.03778 0.03246 0.0152 0.1773 1.0000
15.750 1.4634 0.03997 0.03471 0.0152 0.1750 1.0000
16.000 1.4666 0.04210 0.03692 0.0151 0.1726 1.0000
16.250 1.4678 0.04448 0.03937 0.0149 0.1701 1.0000
16.500 1.4651 0.04730 0.04225 0.0146 0.1672 1.0000
16.750 1.4590 0.05054 0.04551 0.0141 0.1644 1.0000
17.000 1.4574 0.05337 0.04841 0.0136 0.1620 1.0000
17.250 1.4555 0.05630 0.05142 0.0130 0.1592 1.0000
17.500 1.4486 0.05984 0.05503 0.0122 0.1558 1.0000
17.750 1.4393 0.06368 0.05891 0.0113 0.1529 1.0000
18.000 1.4317 0.06739 0.06268 0.0104 0.1495 1.0000
18.250 1.4242 0.07115 0.06652 0.0094 0.1462 1.0000
18.500 1.4119 0.07556 0.07097 0.0081 0.1426 1.0000
18.750 1.3984 0.08015 0.07561 0.0067 0.1391 1.0000
19.000 1.3915 0.08397 0.07950 0.0056 0.1358 1.0000
19.250 1.3769 0.08886 0.08444 0.0040 0.1318 1.0000
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