EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1214 AIRFOIL (e1214-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.93 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1214-il-1000000-n5.txt Download as CSV file: xf-e1214-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.9924 0.08945 0.08528 -0.0311 1.0000 0.0138
-17.750 -0.9974 0.08544 0.08122 -0.0328 1.0000 0.0139
-17.500 -1.0059 0.08099 0.07670 -0.0346 1.0000 0.0140
-17.250 -1.0132 0.07680 0.07244 -0.0364 1.0000 0.0140
-17.000 -1.0184 0.07289 0.06847 -0.0379 1.0000 0.0142
-16.750 -1.0292 0.06833 0.06384 -0.0398 1.0000 0.0142
-16.500 -1.0370 0.06427 0.05971 -0.0415 1.0000 0.0143
-16.250 -1.0492 0.05982 0.05517 -0.0432 1.0000 0.0143
-16.000 -1.0593 0.05572 0.05100 -0.0448 1.0000 0.0144
-15.750 -1.0726 0.05126 0.04644 -0.0464 1.0000 0.0144
-15.500 -1.0817 0.04727 0.04237 -0.0479 1.0000 0.0145
-15.250 -1.0935 0.04296 0.03797 -0.0496 1.0000 0.0145
-15.000 -1.1047 0.03865 0.03357 -0.0513 1.0000 0.0147
-14.750 -1.1092 0.03512 0.02995 -0.0527 1.0000 0.0148
-14.500 -1.1132 0.03167 0.02641 -0.0542 1.0000 0.0150
-14.250 -1.1143 0.02873 0.02340 -0.0552 1.0000 0.0152
-14.000 -1.1132 0.02632 0.02092 -0.0556 1.0000 0.0154
-13.750 -1.1105 0.02442 0.01895 -0.0554 1.0000 0.0155
-13.500 -1.1071 0.02288 0.01735 -0.0544 1.0000 0.0157
-13.250 -1.1026 0.02168 0.01611 -0.0528 1.0000 0.0159
-13.000 -1.0980 0.02069 0.01508 -0.0507 1.0000 0.0162
-12.750 -1.0669 0.01975 0.01410 -0.0529 0.9607 0.0166
-12.500 -0.9951 0.01898 0.01295 -0.0625 0.8331 0.0172
-12.250 -0.9913 0.01849 0.01227 -0.0591 0.7852 0.0175
-12.000 -0.9851 0.01799 0.01163 -0.0559 0.7532 0.0180
-11.750 -0.9766 0.01753 0.01107 -0.0529 0.7304 0.0184
-11.500 -0.9667 0.01717 0.01061 -0.0500 0.7092 0.0190
-11.250 -0.9527 0.01682 0.01018 -0.0478 0.6902 0.0195
-11.000 -0.9359 0.01646 0.00974 -0.0460 0.6726 0.0203
-10.750 -0.9185 0.01606 0.00929 -0.0443 0.6580 0.0214
-10.500 -0.8998 0.01570 0.00887 -0.0428 0.6433 0.0230
-10.000 -0.8609 0.01494 0.00803 -0.0400 0.6159 0.0282
-9.750 -0.8407 0.01456 0.00762 -0.0387 0.6038 0.0325
-9.500 -0.8199 0.01416 0.00721 -0.0375 0.5917 0.0384
-9.250 -0.7990 0.01376 0.00680 -0.0363 0.5805 0.0457
-9.000 -0.7770 0.01340 0.00644 -0.0353 0.5694 0.0529
-8.750 -0.7553 0.01300 0.00605 -0.0342 0.5595 0.0623
-8.500 -0.7329 0.01261 0.00569 -0.0332 0.5494 0.0732
-8.250 -0.7104 0.01223 0.00534 -0.0322 0.5398 0.0863
-8.000 -0.6876 0.01184 0.00499 -0.0313 0.5293 0.1005
-7.750 -0.6642 0.01149 0.00468 -0.0305 0.5206 0.1156
-7.500 -0.6404 0.01113 0.00437 -0.0297 0.5116 0.1309
-7.250 -0.6160 0.01084 0.00411 -0.0289 0.5020 0.1457
-7.000 -0.5911 0.01055 0.00387 -0.0283 0.4935 0.1621
-6.750 -0.5663 0.01027 0.00365 -0.0276 0.4848 0.1803
-6.500 -0.5403 0.01006 0.00348 -0.0271 0.4780 0.1948
-6.250 -0.5137 0.00991 0.00333 -0.0267 0.4696 0.2071
-6.000 -0.4868 0.00979 0.00322 -0.0263 0.4613 0.2171
-5.750 -0.4597 0.00966 0.00311 -0.0259 0.4533 0.2277
-5.500 -0.4321 0.00961 0.00302 -0.0257 0.4453 0.2348
-5.250 -0.4045 0.00952 0.00292 -0.0253 0.4392 0.2413
-5.000 -0.3767 0.00945 0.00285 -0.0251 0.4324 0.2478
-4.750 -0.3486 0.00944 0.00278 -0.0249 0.4247 0.2516
-4.500 -0.3207 0.00937 0.00270 -0.0246 0.4182 0.2562
-4.250 -0.2928 0.00932 0.00263 -0.0244 0.4107 0.2605
-4.000 -0.2647 0.00931 0.00258 -0.0241 0.4040 0.2645
-3.750 -0.2362 0.00928 0.00253 -0.0240 0.3991 0.2676
-3.500 -0.2081 0.00925 0.00247 -0.0238 0.3928 0.2718
-3.000 -0.1519 0.00921 0.00239 -0.0233 0.3804 0.2801
-2.750 -0.1235 0.00920 0.00235 -0.0232 0.3744 0.2831
-2.500 -0.0952 0.00922 0.00232 -0.0230 0.3685 0.2857
-2.250 -0.0669 0.00920 0.00229 -0.0228 0.3640 0.2893
-2.000 -0.0387 0.00918 0.00226 -0.0226 0.3587 0.2930
-1.750 -0.0106 0.00919 0.00225 -0.0224 0.3525 0.2964
-1.500 0.0177 0.00921 0.00224 -0.0223 0.3475 0.2996
-1.250 0.0463 0.00921 0.00223 -0.0221 0.3436 0.3026
-1.000 0.0746 0.00922 0.00222 -0.0220 0.3388 0.3057
-0.750 0.1025 0.00924 0.00222 -0.0218 0.3334 0.3101
-0.500 0.1307 0.00925 0.00223 -0.0216 0.3289 0.3138
-0.250 0.1591 0.00926 0.00224 -0.0215 0.3253 0.3174
0.000 0.1875 0.00929 0.00225 -0.0213 0.3214 0.3206
0.250 0.2157 0.00934 0.00227 -0.0212 0.3170 0.3236
0.500 0.2435 0.00937 0.00229 -0.0210 0.3124 0.3288
0.750 0.2718 0.00937 0.00232 -0.0208 0.3093 0.3335
1.000 0.3000 0.00940 0.00235 -0.0207 0.3057 0.3376
1.250 0.3281 0.00945 0.00238 -0.0205 0.3020 0.3410
1.500 0.3559 0.00951 0.00242 -0.0203 0.2983 0.3451
1.750 0.3837 0.00954 0.00247 -0.0201 0.2950 0.3506
2.000 0.4118 0.00957 0.00252 -0.0200 0.2921 0.3564
2.250 0.4398 0.00962 0.00257 -0.0198 0.2887 0.3612
2.500 0.4675 0.00967 0.00262 -0.0196 0.2852 0.3668
2.750 0.4950 0.00973 0.00269 -0.0194 0.2818 0.3730
3.000 0.5225 0.00980 0.00277 -0.0192 0.2786 0.3789
3.250 0.5504 0.00984 0.00283 -0.0190 0.2766 0.3859
3.500 0.5779 0.00988 0.00290 -0.0188 0.2738 0.3947
3.750 0.6054 0.00995 0.00298 -0.0186 0.2706 0.4021
4.000 0.6323 0.01002 0.00307 -0.0183 0.2671 0.4108
4.250 0.6592 0.01011 0.00317 -0.0180 0.2638 0.4201
4.500 0.6863 0.01016 0.00327 -0.0177 0.2616 0.4307
4.750 0.7135 0.01021 0.00337 -0.0175 0.2596 0.4436
5.000 0.7403 0.01026 0.00347 -0.0172 0.2572 0.4580
5.250 0.7670 0.01033 0.00358 -0.0169 0.2544 0.4717
5.500 0.7932 0.01042 0.00370 -0.0165 0.2514 0.4869
5.750 0.8189 0.01052 0.00384 -0.0161 0.2479 0.5048
6.000 0.8450 0.01057 0.00397 -0.0157 0.2457 0.5267
6.250 0.8710 0.01062 0.00410 -0.0153 0.2437 0.5516
6.500 0.8966 0.01066 0.00424 -0.0148 0.2414 0.5785
6.750 0.9217 0.01073 0.00439 -0.0143 0.2389 0.6066
7.000 0.9463 0.01080 0.00455 -0.0137 0.2363 0.6380
7.250 0.9699 0.01088 0.00473 -0.0129 0.2336 0.6757
7.500 0.9929 0.01092 0.00491 -0.0119 0.2312 0.7227
7.750 1.0151 0.01089 0.00508 -0.0108 0.2295 0.7787
8.000 1.0357 0.01085 0.00526 -0.0093 0.2272 0.8446
8.500 1.1333 0.01123 0.00588 -0.0181 0.2211 0.9758
8.750 1.1678 0.01150 0.00613 -0.0196 0.2183 0.9861
9.000 1.1969 0.01172 0.00637 -0.0200 0.2162 0.9927
9.250 1.2297 0.01193 0.00659 -0.0212 0.2142 0.9974
9.500 1.2638 0.01216 0.00683 -0.0227 0.2118 1.0000
9.750 1.2832 0.01238 0.00705 -0.0212 0.2097 1.0000
10.000 1.3018 0.01262 0.00728 -0.0196 0.2074 1.0000
10.250 1.3194 0.01288 0.00755 -0.0179 0.2049 1.0000
10.500 1.3366 0.01315 0.00783 -0.0161 0.2025 1.0000
10.750 1.3552 0.01337 0.00807 -0.0145 0.2009 1.0000
11.000 1.3715 0.01361 0.00833 -0.0125 0.1988 1.0000
11.250 1.3841 0.01386 0.00860 -0.0099 0.1965 1.0000
11.500 1.3963 0.01417 0.00891 -0.0074 0.1942 1.0000
11.750 1.4082 0.01454 0.00929 -0.0049 0.1917 1.0000
12.000 1.4203 0.01497 0.00972 -0.0027 0.1891 1.0000
12.250 1.4363 0.01530 0.01009 -0.0011 0.1876 1.0000
12.500 1.4514 0.01570 0.01052 0.0006 0.1856 1.0000
12.750 1.4655 0.01617 0.01103 0.0021 0.1834 1.0000
13.000 1.4784 0.01675 0.01163 0.0037 0.1811 1.0000
13.250 1.4901 0.01746 0.01235 0.0052 0.1786 1.0000
13.500 1.5002 0.01832 0.01323 0.0066 0.1761 1.0000
13.750 1.5148 0.01901 0.01397 0.0075 0.1745 1.0000
14.000 1.5281 0.01983 0.01484 0.0083 0.1724 1.0000
14.250 1.5399 0.02082 0.01586 0.0091 0.1699 1.0000
14.500 1.5493 0.02204 0.01711 0.0098 0.1671 1.0000
14.750 1.5548 0.02364 0.01872 0.0104 0.1635 1.0000
15.000 1.5659 0.02486 0.01999 0.0107 0.1612 1.0000
15.250 1.5734 0.02643 0.02160 0.0111 0.1574 1.0000
15.500 1.5773 0.02834 0.02354 0.0113 0.1543 1.0000
15.750 1.5779 0.03059 0.02583 0.0115 0.1506 1.0000
16.000 1.5816 0.03260 0.02789 0.0116 0.1474 1.0000
16.250 1.5818 0.03496 0.03029 0.0116 0.1443 1.0000
16.500 1.5720 0.03830 0.03367 0.0115 0.1399 1.0000
16.750 1.5713 0.04082 0.03624 0.0114 0.1372 1.0000
17.000 1.5670 0.04375 0.03923 0.0112 0.1344 1.0000
17.250 1.5546 0.04760 0.04312 0.0107 0.1306 1.0000
17.500 1.5439 0.05136 0.04694 0.0101 0.1275 1.0000
17.750 1.5349 0.05501 0.05065 0.0095 0.1244 1.0000
18.000 1.5182 0.05959 0.05528 0.0086 0.1206 1.0000
18.250 1.4981 0.06465 0.06040 0.0075 0.1163 1.0000
18.500 1.4828 0.06923 0.06503 0.0064 0.1127 1.0000
18.750 1.4601 0.07477 0.07062 0.0049 0.1092 1.0000
19.000 1.4447 0.07954 0.07546 0.0036 0.1058 1.0000
19.250 1.4230 0.08514 0.08111 0.0020 0.1019 1.0000
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Polar data table (+)
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