EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1213 AIRFOIL (e1213-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.92 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1213-il-1000000.txt Download as CSV file: xf-e1213-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1213 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.9936 0.08759 0.08379 -0.0245 1.0000 0.0202
-16.750 -1.0088 0.08204 0.07817 -0.0272 1.0000 0.0202
-16.500 -1.0239 0.07661 0.07267 -0.0299 1.0000 0.0203
-16.250 -1.0463 0.07046 0.06641 -0.0330 1.0000 0.0204
-16.000 -1.0750 0.06357 0.05942 -0.0365 1.0000 0.0204
-15.750 -1.1096 0.05595 0.05166 -0.0405 1.0000 0.0202
-15.500 -1.1426 0.04835 0.04391 -0.0446 1.0000 0.0203
-15.250 -1.1705 0.04102 0.03642 -0.0490 1.0000 0.0202
-15.000 -1.1876 0.03496 0.03020 -0.0531 1.0000 0.0203
-14.750 -1.1967 0.03054 0.02563 -0.0559 1.0000 0.0204
-14.500 -1.2015 0.02752 0.02251 -0.0570 1.0000 0.0205
-14.250 -1.2034 0.02546 0.02034 -0.0565 1.0000 0.0206
-14.000 -1.2078 0.02371 0.01850 -0.0546 1.0000 0.0209
-13.750 -1.2098 0.02241 0.01713 -0.0518 1.0000 0.0211
-13.500 -1.2087 0.02145 0.01611 -0.0486 1.0000 0.0214
-13.250 -1.2038 0.02061 0.01522 -0.0456 1.0000 0.0218
-13.000 -1.1914 0.01988 0.01445 -0.0436 1.0000 0.0221
-12.750 -1.1771 0.01919 0.01373 -0.0418 1.0000 0.0226
-12.500 -1.1610 0.01858 0.01307 -0.0401 1.0000 0.0231
-12.250 -1.1435 0.01802 0.01247 -0.0386 1.0000 0.0236
-12.000 -1.1266 0.01739 0.01182 -0.0370 1.0000 0.0244
-11.750 -1.1093 0.01677 0.01119 -0.0354 1.0000 0.0254
-11.500 -1.0909 0.01623 0.01062 -0.0338 1.0000 0.0267
-11.250 -1.0725 0.01567 0.01006 -0.0323 1.0000 0.0284
-10.750 -1.0378 0.01439 0.00883 -0.0288 1.0000 0.0387
-10.500 -1.0190 0.01351 0.00806 -0.0276 0.9989 0.0534
-10.250 -0.9838 0.01264 0.00732 -0.0296 0.9870 0.0709
-10.000 -0.9399 0.01188 0.00667 -0.0331 0.9538 0.0882
-9.750 -0.9021 0.01148 0.00617 -0.0351 0.8814 0.1011
-9.500 -0.8802 0.01126 0.00585 -0.0337 0.8349 0.1102
-9.250 -0.8565 0.01107 0.00557 -0.0327 0.8027 0.1181
-9.000 -0.8313 0.01089 0.00532 -0.0320 0.7767 0.1253
-8.750 -0.8063 0.01067 0.00507 -0.0313 0.7537 0.1334
-8.500 -0.7801 0.01052 0.00485 -0.0307 0.7332 0.1398
-8.250 -0.7539 0.01035 0.00465 -0.0302 0.7145 0.1468
-8.000 -0.7271 0.01022 0.00446 -0.0297 0.6966 0.1528
-7.750 -0.7004 0.01007 0.00429 -0.0292 0.6807 0.1593
-7.500 -0.6729 0.01001 0.00415 -0.0289 0.6648 0.1639
-7.250 -0.6458 0.00985 0.00398 -0.0284 0.6499 0.1698
-7.000 -0.6180 0.00977 0.00386 -0.0281 0.6364 0.1747
-6.750 -0.5902 0.00971 0.00373 -0.0278 0.6227 0.1787
-6.500 -0.5627 0.00959 0.00360 -0.0275 0.6093 0.1844
-6.250 -0.5345 0.00953 0.00350 -0.0272 0.5974 0.1891
-6.000 -0.5061 0.00953 0.00342 -0.0269 0.5846 0.1924
-5.750 -0.4784 0.00939 0.00329 -0.0266 0.5731 0.1980
-5.500 -0.4503 0.00934 0.00320 -0.0264 0.5623 0.2020
-5.250 -0.4217 0.00932 0.00313 -0.0261 0.5509 0.2057
-5.000 -0.3931 0.00930 0.00305 -0.0259 0.5403 0.2086
-4.750 -0.3654 0.00919 0.00293 -0.0256 0.5296 0.2137
-4.500 -0.3370 0.00913 0.00286 -0.0254 0.5201 0.2173
-4.250 -0.3085 0.00912 0.00279 -0.0252 0.5095 0.2203
-4.000 -0.2797 0.00910 0.00272 -0.0250 0.5001 0.2227
-3.750 -0.2513 0.00907 0.00264 -0.0248 0.4905 0.2252
-3.500 -0.2232 0.00897 0.00254 -0.0245 0.4820 0.2298
-3.250 -0.1949 0.00894 0.00248 -0.0243 0.4723 0.2332
-3.000 -0.1662 0.00892 0.00243 -0.0241 0.4638 0.2365
-2.750 -0.1375 0.00892 0.00239 -0.0240 0.4551 0.2392
-2.500 -0.1087 0.00893 0.00235 -0.0238 0.4468 0.2410
-2.250 -0.0806 0.00885 0.00226 -0.0236 0.4383 0.2460
-2.000 -0.0523 0.00883 0.00223 -0.0233 0.4297 0.2501
-1.750 -0.0236 0.00880 0.00219 -0.0232 0.4226 0.2536
-1.500 0.0050 0.00883 0.00217 -0.0230 0.4139 0.2566
-1.250 0.0339 0.00884 0.00215 -0.0229 0.4067 0.2590
-1.000 0.0620 0.00879 0.00210 -0.0226 0.3989 0.2649
-0.750 0.0904 0.00879 0.00209 -0.0224 0.3913 0.2693
-0.500 0.1191 0.00879 0.00208 -0.0223 0.3840 0.2734
-0.250 0.1475 0.00885 0.00208 -0.0221 0.3757 0.2767
0.000 0.1760 0.00880 0.00206 -0.0219 0.3696 0.2834
0.250 0.2043 0.00881 0.00207 -0.0218 0.3623 0.2892
0.500 0.2328 0.00885 0.00209 -0.0216 0.3556 0.2942
0.750 0.2613 0.00884 0.00209 -0.0214 0.3496 0.3016
1.000 0.2894 0.00887 0.00211 -0.0212 0.3424 0.3098
1.250 0.3178 0.00889 0.00214 -0.0211 0.3362 0.3180
1.500 0.3460 0.00888 0.00217 -0.0209 0.3303 0.3287
1.750 0.3739 0.00893 0.00221 -0.0207 0.3236 0.3402
2.250 0.4302 0.00893 0.00230 -0.0203 0.3129 0.3718
2.500 0.4577 0.00897 0.00237 -0.0200 0.3063 0.3917
3.000 0.5133 0.00895 0.00249 -0.0196 0.2960 0.4403
3.250 0.5405 0.00898 0.00258 -0.0193 0.2902 0.4706
3.500 0.5678 0.00897 0.00267 -0.0190 0.2854 0.5056
3.750 0.5949 0.00892 0.00275 -0.0187 0.2809 0.5488
4.000 0.6214 0.00890 0.00286 -0.0182 0.2757 0.5981
4.250 0.6471 0.00889 0.00299 -0.0177 0.2699 0.6521
4.500 0.6730 0.00880 0.00309 -0.0171 0.2660 0.7126
4.750 0.6974 0.00872 0.00321 -0.0161 0.2614 0.7819
5.000 0.7196 0.00863 0.00337 -0.0147 0.2564 0.8679
5.250 0.7667 0.00868 0.00359 -0.0182 0.2515 0.9568
5.750 0.8476 0.00907 0.00390 -0.0232 0.2408 0.9887
6.000 0.8864 0.00924 0.00406 -0.0253 0.2361 0.9946
6.250 0.9286 0.00939 0.00419 -0.0282 0.2314 0.9989
6.500 0.9588 0.00959 0.00435 -0.0286 0.2269 1.0000
6.750 0.9814 0.00982 0.00455 -0.0276 0.2222 1.0000
7.000 1.0058 0.00995 0.00468 -0.0267 0.2197 1.0000
7.250 1.0297 0.01011 0.00484 -0.0258 0.2164 1.0000
7.500 1.0530 0.01032 0.00502 -0.0249 0.2127 1.0000
7.750 1.0753 0.01059 0.00526 -0.0238 0.2082 1.0000
8.000 1.0992 0.01076 0.00544 -0.0229 0.2056 1.0000
8.250 1.1232 0.01093 0.00562 -0.0221 0.2029 1.0000
8.500 1.1465 0.01114 0.00582 -0.0212 0.1999 1.0000
8.750 1.1691 0.01139 0.00605 -0.0202 0.1967 1.0000
9.000 1.1902 0.01173 0.00636 -0.0190 0.1928 1.0000
9.250 1.2141 0.01190 0.00656 -0.0182 0.1912 1.0000
9.500 1.2376 0.01209 0.00677 -0.0173 0.1890 1.0000
9.750 1.2604 0.01232 0.00701 -0.0164 0.1865 1.0000
10.000 1.2824 0.01259 0.00728 -0.0154 0.1840 1.0000
10.250 1.3032 0.01293 0.00760 -0.0142 0.1809 1.0000
10.500 1.3235 0.01328 0.00796 -0.0130 0.1782 1.0000
10.750 1.3466 0.01348 0.00819 -0.0122 0.1767 1.0000
11.000 1.3689 0.01371 0.00845 -0.0113 0.1747 1.0000
11.250 1.3900 0.01399 0.00875 -0.0102 0.1726 1.0000
11.500 1.4098 0.01432 0.00908 -0.0090 0.1703 1.0000
11.750 1.4275 0.01473 0.00949 -0.0075 0.1677 1.0000
12.000 1.4421 0.01522 0.00998 -0.0055 0.1648 1.0000
12.250 1.4606 0.01546 0.01027 -0.0041 0.1636 1.0000
12.500 1.4769 0.01575 0.01060 -0.0022 0.1621 1.0000
12.750 1.4918 0.01610 0.01098 -0.0003 0.1603 1.0000
13.000 1.5055 0.01652 0.01143 0.0016 0.1582 1.0000
13.250 1.5173 0.01707 0.01199 0.0036 0.1560 1.0000
13.500 1.5249 0.01786 0.01279 0.0058 0.1531 1.0000
13.750 1.5359 0.01858 0.01355 0.0074 0.1515 1.0000
14.000 1.5529 0.01907 0.01410 0.0083 0.1496 1.0000
14.250 1.5665 0.01977 0.01485 0.0094 0.1478 1.0000
14.500 1.5780 0.02067 0.01578 0.0104 0.1458 1.0000
14.750 1.5870 0.02182 0.01695 0.0113 0.1432 1.0000
15.000 1.5923 0.02335 0.01851 0.0121 0.1407 1.0000
15.250 1.6012 0.02471 0.01992 0.0127 0.1391 1.0000
15.500 1.6143 0.02579 0.02106 0.0130 0.1373 1.0000
15.750 1.6246 0.02714 0.02247 0.0132 0.1353 1.0000
16.000 1.6317 0.02882 0.02419 0.0134 0.1331 1.0000
16.250 1.6348 0.03092 0.02633 0.0134 0.1308 1.0000
16.500 1.6323 0.03362 0.02906 0.0133 0.1280 1.0000
16.750 1.6404 0.03531 0.03083 0.0132 0.1262 1.0000
17.000 1.6445 0.03742 0.03300 0.0131 0.1239 1.0000
17.250 1.6439 0.04001 0.03565 0.0128 0.1217 1.0000
17.500 1.6388 0.04308 0.03877 0.0124 0.1196 1.0000
17.750 1.6277 0.04686 0.04259 0.0117 0.1170 1.0000
18.000 1.6282 0.04946 0.04527 0.0113 0.1146 1.0000
18.250 1.6218 0.05287 0.04874 0.0105 0.1118 1.0000
18.500 1.6099 0.05699 0.05291 0.0095 0.1091 1.0000
18.750 1.5937 0.06167 0.05764 0.0082 0.1064 1.0000
19.000 1.5873 0.06528 0.06133 0.0073 0.1042 1.0000
19.250 1.5744 0.06969 0.06580 0.0060 0.1013 1.0000
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Polar data table (+)
Polar graphs
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