EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1213 AIRFOIL (e1213-il) Reynolds number: 500,000 Max Cl/Cd: 80.23 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1213-il-500000-n5.txt Download as CSV file: xf-e1213-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9353 0.08553 0.08091 -0.0250 1.0000 0.0210
-16.000 -0.9484 0.08017 0.07548 -0.0277 1.0000 0.0211
-15.750 -0.9656 0.07445 0.06968 -0.0306 1.0000 0.0212
-15.500 -0.9884 0.06824 0.06337 -0.0338 1.0000 0.0213
-15.250 -1.0116 0.06207 0.05709 -0.0369 1.0000 0.0213
-15.000 -1.0390 0.05536 0.05025 -0.0403 1.0000 0.0213
-14.750 -1.0664 0.04855 0.04330 -0.0439 1.0000 0.0214
-14.500 -1.0881 0.04223 0.03683 -0.0475 1.0000 0.0213
-14.250 -1.1057 0.03636 0.03079 -0.0512 1.0000 0.0214
-14.000 -1.1180 0.03178 0.02607 -0.0540 1.0000 0.0217
-13.750 -1.1251 0.02874 0.02291 -0.0547 1.0000 0.0219
-13.500 -1.1281 0.02671 0.02078 -0.0539 1.0000 0.0222
-13.250 -1.1284 0.02523 0.01923 -0.0521 1.0000 0.0226
-13.000 -1.1256 0.02413 0.01806 -0.0498 1.0000 0.0229
-12.750 -1.1216 0.02322 0.01709 -0.0470 1.0000 0.0235
-12.500 -1.1138 0.02239 0.01620 -0.0445 1.0000 0.0241
-12.250 -1.1027 0.02153 0.01531 -0.0425 1.0000 0.0249
-12.000 -1.0891 0.02077 0.01451 -0.0408 1.0000 0.0260
-11.750 -1.0735 0.02008 0.01379 -0.0391 1.0000 0.0273
-11.500 -1.0583 0.01933 0.01302 -0.0375 1.0000 0.0296
-11.250 -1.0420 0.01863 0.01232 -0.0359 1.0000 0.0325
-11.000 -1.0257 0.01791 0.01161 -0.0342 1.0000 0.0376
-10.750 -1.0059 0.01720 0.01092 -0.0332 0.9975 0.0444
-10.500 -0.9697 0.01629 0.01006 -0.0356 0.9525 0.0555
-10.250 -0.9247 0.01547 0.00918 -0.0395 0.8808 0.0690
-10.000 -0.9049 0.01504 0.00863 -0.0380 0.8324 0.0788
-9.750 -0.8841 0.01465 0.00816 -0.0367 0.7999 0.0882
-9.500 -0.8619 0.01429 0.00773 -0.0357 0.7738 0.0974
-9.250 -0.8386 0.01398 0.00736 -0.0348 0.7511 0.1056
-9.000 -0.8145 0.01370 0.00701 -0.0340 0.7306 0.1135
-8.750 -0.7901 0.01342 0.00669 -0.0332 0.7121 0.1213
-8.500 -0.7651 0.01316 0.00639 -0.0325 0.6948 0.1294
-8.250 -0.7395 0.01296 0.00612 -0.0320 0.6789 0.1373
-8.000 -0.7140 0.01273 0.00587 -0.0314 0.6637 0.1452
-7.750 -0.6876 0.01256 0.00565 -0.0309 0.6487 0.1517
-7.500 -0.6613 0.01239 0.00544 -0.0304 0.6351 0.1583
-7.250 -0.6343 0.01227 0.00525 -0.0299 0.6217 0.1640
-7.000 -0.6077 0.01211 0.00507 -0.0295 0.6087 0.1698
-6.750 -0.5804 0.01200 0.00490 -0.0291 0.5967 0.1757
-6.500 -0.5533 0.01189 0.00474 -0.0287 0.5844 0.1810
-6.250 -0.5259 0.01178 0.00460 -0.0284 0.5729 0.1867
-6.000 -0.4982 0.01172 0.00446 -0.0280 0.5620 0.1913
-5.750 -0.4708 0.01161 0.00432 -0.0277 0.5504 0.1954
-5.500 -0.4432 0.01151 0.00418 -0.0273 0.5404 0.1992
-5.250 -0.4155 0.01144 0.00406 -0.0270 0.5298 0.2029
-5.000 -0.3875 0.01138 0.00393 -0.0267 0.5198 0.2061
-4.750 -0.3596 0.01132 0.00380 -0.0264 0.5096 0.2089
-4.500 -0.3319 0.01122 0.00369 -0.0261 0.5008 0.2126
-4.250 -0.3041 0.01116 0.00358 -0.0258 0.4908 0.2160
-4.000 -0.2760 0.01111 0.00349 -0.0255 0.4819 0.2193
-3.750 -0.2478 0.01107 0.00339 -0.0253 0.4729 0.2224
-3.500 -0.2198 0.01103 0.00330 -0.0250 0.4645 0.2253
-3.250 -0.1919 0.01096 0.00321 -0.0247 0.4553 0.2286
-3.000 -0.1640 0.01092 0.00313 -0.0244 0.4472 0.2321
-2.750 -0.1357 0.01088 0.00307 -0.0242 0.4393 0.2358
-2.250 -0.0792 0.01085 0.00294 -0.0237 0.4230 0.2414
-2.000 -0.0514 0.01080 0.00288 -0.0234 0.4151 0.2454
-1.750 -0.0234 0.01078 0.00285 -0.0232 0.4083 0.2494
-1.500 0.0049 0.01076 0.00281 -0.0230 0.4004 0.2531
-1.250 0.0329 0.01078 0.00277 -0.0227 0.3928 0.2565
-1.000 0.0613 0.01077 0.00275 -0.0225 0.3860 0.2601
-0.750 0.0891 0.01075 0.00272 -0.0223 0.3787 0.2647
-0.500 0.1172 0.01075 0.00272 -0.0220 0.3718 0.2691
-0.250 0.1454 0.01076 0.00271 -0.0218 0.3647 0.2734
0.000 0.1733 0.01081 0.00271 -0.0216 0.3577 0.2777
0.250 0.2013 0.01079 0.00271 -0.0213 0.3513 0.2836
0.500 0.2293 0.01081 0.00273 -0.0211 0.3442 0.2894
0.750 0.2572 0.01086 0.00275 -0.0209 0.3378 0.2947
1.000 0.2852 0.01086 0.00278 -0.0206 0.3314 0.3010
1.250 0.3129 0.01090 0.00281 -0.0204 0.3249 0.3089
1.500 0.3406 0.01094 0.00286 -0.0201 0.3197 0.3170
1.750 0.3685 0.01095 0.00291 -0.0199 0.3140 0.3269
2.000 0.3961 0.01101 0.00296 -0.0196 0.3077 0.3362
2.250 0.4235 0.01105 0.00303 -0.0194 0.3022 0.3480
2.500 0.4512 0.01108 0.00310 -0.0191 0.2969 0.3606
2.750 0.4785 0.01113 0.00318 -0.0188 0.2916 0.3760
3.000 0.5055 0.01119 0.00328 -0.0185 0.2867 0.3949
3.250 0.5329 0.01120 0.00337 -0.0182 0.2821 0.4158
3.500 0.5599 0.01123 0.00347 -0.0179 0.2766 0.4386
3.750 0.5863 0.01130 0.00359 -0.0175 0.2711 0.4647
4.250 0.6396 0.01132 0.00384 -0.0168 0.2624 0.5321
4.500 0.6653 0.01134 0.00398 -0.0162 0.2578 0.5759
4.750 0.6903 0.01136 0.00414 -0.0156 0.2536 0.6247
5.000 0.7156 0.01133 0.00430 -0.0149 0.2497 0.6771
5.250 0.7397 0.01130 0.00446 -0.0140 0.2452 0.7364
5.500 0.7620 0.01126 0.00464 -0.0127 0.2406 0.8101
5.750 0.7933 0.01125 0.00490 -0.0130 0.2364 0.9104
6.000 0.8522 0.01148 0.00516 -0.0192 0.2312 0.9695
6.250 0.8886 0.01171 0.00537 -0.0210 0.2266 0.9862
6.500 0.9236 0.01199 0.00560 -0.0225 0.2224 0.9965
6.750 0.9546 0.01218 0.00580 -0.0231 0.2190 1.0000
7.000 0.9778 0.01239 0.00600 -0.0222 0.2153 1.0000
7.250 1.0005 0.01263 0.00622 -0.0211 0.2115 1.0000
7.500 1.0226 0.01291 0.00647 -0.0201 0.2081 1.0000
7.750 1.0455 0.01313 0.00670 -0.0191 0.2055 1.0000
8.000 1.0685 0.01335 0.00694 -0.0182 0.2028 1.0000
8.250 1.0911 0.01360 0.00719 -0.0172 0.1999 1.0000
8.500 1.1131 0.01388 0.00747 -0.0161 0.1969 1.0000
8.750 1.1344 0.01421 0.00777 -0.0150 0.1939 1.0000
9.000 1.1563 0.01449 0.00807 -0.0140 0.1914 1.0000
9.250 1.1786 0.01475 0.00836 -0.0131 0.1889 1.0000
9.500 1.2003 0.01504 0.00867 -0.0120 0.1865 1.0000
9.750 1.2212 0.01537 0.00900 -0.0109 0.1841 1.0000
10.000 1.2411 0.01573 0.00937 -0.0097 0.1817 1.0000
10.250 1.2597 0.01614 0.00977 -0.0084 0.1792 1.0000
10.500 1.2795 0.01647 0.01014 -0.0071 0.1772 1.0000
10.750 1.2990 0.01680 0.01052 -0.0059 0.1753 1.0000
11.000 1.3170 0.01717 0.01092 -0.0045 0.1733 1.0000
11.250 1.3317 0.01757 0.01135 -0.0025 0.1713 1.0000
11.500 1.3442 0.01804 0.01184 -0.0003 0.1691 1.0000
11.750 1.3555 0.01859 0.01240 0.0019 0.1670 1.0000
12.000 1.3654 0.01925 0.01307 0.0040 0.1649 1.0000
12.250 1.3801 0.01977 0.01366 0.0055 0.1634 1.0000
12.500 1.3935 0.02040 0.01435 0.0069 0.1617 1.0000
12.750 1.4056 0.02115 0.01515 0.0082 0.1596 1.0000
13.000 1.4164 0.02203 0.01608 0.0094 0.1577 1.0000
13.250 1.4256 0.02309 0.01717 0.0105 0.1555 1.0000
13.500 1.4332 0.02436 0.01847 0.0115 0.1535 1.0000
13.750 1.4406 0.02573 0.01988 0.0123 0.1516 1.0000
14.000 1.4522 0.02687 0.02110 0.0128 0.1499 1.0000
14.250 1.4621 0.02819 0.02249 0.0132 0.1480 1.0000
14.500 1.4699 0.02973 0.02409 0.0135 0.1458 1.0000
14.750 1.4753 0.03152 0.02593 0.0138 0.1435 1.0000
15.000 1.4785 0.03357 0.02803 0.0139 0.1415 1.0000
15.250 1.4796 0.03586 0.03035 0.0139 0.1395 1.0000
15.500 1.4862 0.03768 0.03226 0.0139 0.1377 1.0000
15.750 1.4906 0.03974 0.03440 0.0138 0.1358 1.0000
16.000 1.4920 0.04213 0.03686 0.0136 0.1334 1.0000
16.250 1.4897 0.04494 0.03972 0.0132 0.1310 1.0000
16.500 1.4856 0.04798 0.04281 0.0127 0.1290 1.0000
16.750 1.4827 0.05098 0.04588 0.0121 0.1267 1.0000
17.000 1.4824 0.05379 0.04878 0.0115 0.1245 1.0000
17.250 1.4783 0.05710 0.05216 0.0106 0.1217 1.0000
17.500 1.4723 0.06068 0.05580 0.0096 0.1197 1.0000
17.750 1.4599 0.06516 0.06032 0.0082 0.1167 1.0000
18.000 1.4578 0.06838 0.06363 0.0072 0.1144 1.0000
18.250 1.4515 0.07220 0.06753 0.0060 0.1120 1.0000
18.500 1.4413 0.07663 0.07202 0.0044 0.1093 1.0000
18.750 1.4258 0.08181 0.07724 0.0024 0.1065 1.0000
19.000 1.4184 0.08599 0.08151 0.0009 0.1034 1.0000
19.250 1.4085 0.09058 0.08616 -0.0009 0.1007 1.0000
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