EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1213 AIRFOIL (e1213-il) Reynolds number: 200,000 Max Cl/Cd: 55.85 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1213-il-200000-n5.txt Download as CSV file: xf-e1213-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8384 0.09075 0.08527 -0.0214 1.0000 0.0386
-15.250 -0.8474 0.08581 0.08027 -0.0239 1.0000 0.0396
-15.000 -0.8638 0.07991 0.07432 -0.0270 1.0000 0.0406
-14.750 -0.8834 0.07387 0.06821 -0.0302 1.0000 0.0414
-14.500 -0.9043 0.06778 0.06204 -0.0334 1.0000 0.0419
-14.250 -0.9287 0.06128 0.05543 -0.0368 1.0000 0.0425
-14.000 -0.9549 0.05457 0.04860 -0.0404 1.0000 0.0432
-13.750 -0.9800 0.04793 0.04181 -0.0443 1.0000 0.0440
-13.500 -0.9998 0.04199 0.03571 -0.0479 1.0000 0.0446
-13.250 -1.0186 0.03662 0.03020 -0.0512 1.0000 0.0457
-13.000 -1.0310 0.03294 0.02639 -0.0525 1.0000 0.0472
-12.750 -1.0390 0.03045 0.02379 -0.0520 1.0000 0.0500
-12.500 -1.0458 0.02852 0.02181 -0.0501 1.0000 0.0532
-12.250 -1.0485 0.02710 0.02035 -0.0473 1.0000 0.0574
-12.000 -1.0462 0.02586 0.01908 -0.0448 1.0000 0.0630
-11.750 -1.0385 0.02473 0.01793 -0.0428 1.0000 0.0697
-11.500 -1.0281 0.02369 0.01689 -0.0410 1.0000 0.0775
-11.250 -1.0147 0.02280 0.01599 -0.0394 1.0000 0.0856
-11.000 -0.9996 0.02200 0.01519 -0.0379 1.0000 0.0941
-10.750 -0.9832 0.02128 0.01448 -0.0364 1.0000 0.1025
-10.500 -0.9656 0.02064 0.01385 -0.0351 1.0000 0.1107
-10.250 -0.9469 0.02009 0.01330 -0.0338 1.0000 0.1182
-10.000 -0.9271 0.01961 0.01279 -0.0325 1.0000 0.1258
-9.750 -0.9080 0.01915 0.01235 -0.0312 1.0000 0.1325
-9.500 -0.8879 0.01876 0.01193 -0.0299 1.0000 0.1391
-9.250 -0.8508 0.01832 0.01148 -0.0320 0.9728 0.1483
-9.000 -0.8076 0.01797 0.01110 -0.0351 0.9249 0.1582
-8.750 -0.7653 0.01769 0.01070 -0.0378 0.8833 0.1669
-8.500 -0.7345 0.01755 0.01040 -0.0381 0.8450 0.1745
-8.250 -0.7082 0.01742 0.01014 -0.0376 0.8144 0.1807
-8.000 -0.6833 0.01734 0.00994 -0.0368 0.7885 0.1865
-7.750 -0.6582 0.01723 0.00959 -0.0359 0.7658 0.1921
-7.500 -0.6336 0.01707 0.00939 -0.0351 0.7456 0.1962
-7.250 -0.6084 0.01695 0.00916 -0.0343 0.7268 0.2004
-7.000 -0.5828 0.01680 0.00885 -0.0337 0.7092 0.2048
-6.750 -0.5570 0.01663 0.00853 -0.0330 0.6929 0.2087
-6.500 -0.5313 0.01646 0.00832 -0.0324 0.6776 0.2122
-6.250 -0.5053 0.01634 0.00809 -0.0317 0.6630 0.2160
-6.000 -0.4789 0.01620 0.00783 -0.0312 0.6487 0.2201
-5.750 -0.4522 0.01608 0.00754 -0.0307 0.6352 0.2239
-5.500 -0.4260 0.01588 0.00732 -0.0302 0.6226 0.2273
-5.250 -0.3994 0.01574 0.00713 -0.0297 0.6098 0.2308
-5.000 -0.3725 0.01562 0.00691 -0.0292 0.5978 0.2347
-4.750 -0.3456 0.01553 0.00668 -0.0287 0.5862 0.2387
-4.500 -0.3184 0.01538 0.00646 -0.0283 0.5745 0.2422
-4.250 -0.2917 0.01523 0.00628 -0.0279 0.5640 0.2456
-4.000 -0.2645 0.01511 0.00612 -0.0275 0.5528 0.2494
-3.750 -0.2373 0.01503 0.00595 -0.0271 0.5428 0.2536
-3.500 -0.2098 0.01495 0.00577 -0.0267 0.5321 0.2574
-3.250 -0.1827 0.01482 0.00560 -0.0263 0.5226 0.2609
-3.000 -0.1556 0.01471 0.00548 -0.0259 0.5126 0.2649
-2.750 -0.1283 0.01464 0.00536 -0.0255 0.5034 0.2692
-2.500 -0.1008 0.01457 0.00523 -0.0252 0.4938 0.2735
-2.250 -0.0733 0.01453 0.00510 -0.0248 0.4853 0.2776
-2.000 -0.0462 0.01441 0.00502 -0.0245 0.4758 0.2820
-1.750 -0.0191 0.01437 0.00493 -0.0241 0.4677 0.2868
-1.500 0.0086 0.01431 0.00485 -0.0238 0.4589 0.2917
-1.250 0.0359 0.01430 0.00476 -0.0234 0.4508 0.2964
-1.000 0.0631 0.01421 0.00472 -0.0231 0.4425 0.3017
-0.750 0.0903 0.01419 0.00468 -0.0227 0.4344 0.3078
-0.500 0.1178 0.01419 0.00463 -0.0224 0.4270 0.3139
-0.250 0.1450 0.01414 0.00461 -0.0220 0.4188 0.3197
0.000 0.1718 0.01415 0.00459 -0.0216 0.4117 0.3269
0.250 0.1994 0.01414 0.00460 -0.0213 0.4040 0.3350
0.500 0.2262 0.01412 0.00460 -0.0209 0.3967 0.3438
0.750 0.2534 0.01415 0.00462 -0.0205 0.3897 0.3536
1.000 0.2802 0.01413 0.00466 -0.0202 0.3822 0.3639
1.250 0.3068 0.01417 0.00468 -0.0197 0.3757 0.3760
1.500 0.3338 0.01417 0.00475 -0.0194 0.3687 0.3910
1.750 0.3603 0.01417 0.00481 -0.0189 0.3617 0.4082
2.000 0.3864 0.01421 0.00488 -0.0185 0.3557 0.4279
2.250 0.4130 0.01420 0.00499 -0.0180 0.3490 0.4505
2.500 0.4388 0.01423 0.00508 -0.0175 0.3425 0.4764
2.750 0.4644 0.01424 0.00520 -0.0169 0.3369 0.5086
3.000 0.4899 0.01421 0.00534 -0.0163 0.3309 0.5473
3.250 0.5145 0.01420 0.00548 -0.0155 0.3252 0.5929
3.500 0.5386 0.01419 0.00563 -0.0145 0.3199 0.6449
3.750 0.5628 0.01414 0.00582 -0.0135 0.3139 0.7040
4.000 0.5872 0.01410 0.00601 -0.0125 0.3084 0.7761
4.250 0.6230 0.01416 0.00626 -0.0135 0.3030 0.8660
4.500 0.6801 0.01436 0.00655 -0.0191 0.2958 0.9397
4.750 0.7201 0.01461 0.00676 -0.0215 0.2898 0.9775
5.000 0.7611 0.01488 0.00699 -0.0242 0.2840 0.9970
5.250 0.7879 0.01511 0.00720 -0.0240 0.2787 1.0000
5.500 0.8101 0.01536 0.00741 -0.0229 0.2742 1.0000
5.750 0.8317 0.01567 0.00763 -0.0218 0.2703 1.0000
6.000 0.8547 0.01590 0.00790 -0.0208 0.2661 1.0000
6.250 0.8771 0.01617 0.00817 -0.0198 0.2616 1.0000
6.500 0.8991 0.01647 0.00843 -0.0187 0.2574 1.0000
6.750 0.9205 0.01681 0.00870 -0.0176 0.2536 1.0000
7.000 0.9433 0.01709 0.00903 -0.0167 0.2494 1.0000
7.250 0.9654 0.01740 0.00935 -0.0157 0.2455 1.0000
7.500 0.9871 0.01774 0.00967 -0.0147 0.2419 1.0000
7.750 1.0081 0.01813 0.01001 -0.0136 0.2387 1.0000
8.000 1.0299 0.01848 0.01040 -0.0126 0.2354 1.0000
8.250 1.0516 0.01883 0.01080 -0.0116 0.2317 1.0000
8.500 1.0724 0.01921 0.01119 -0.0106 0.2281 1.0000
8.750 1.0925 0.01963 0.01158 -0.0094 0.2249 1.0000
9.000 1.1120 0.02010 0.01201 -0.0083 0.2222 1.0000
9.250 1.1325 0.02051 0.01251 -0.0072 0.2193 1.0000
9.500 1.1521 0.02095 0.01300 -0.0061 0.2164 1.0000
9.750 1.1708 0.02141 0.01350 -0.0048 0.2135 1.0000
10.000 1.1884 0.02190 0.01399 -0.0035 0.2108 1.0000
10.250 1.2049 0.02244 0.01451 -0.0020 0.2083 1.0000
10.500 1.2211 0.02298 0.01509 -0.0006 0.2059 1.0000
10.750 1.2353 0.02352 0.01571 0.0012 0.2035 1.0000
11.000 1.2482 0.02411 0.01637 0.0031 0.2012 1.0000
11.250 1.2604 0.02474 0.01706 0.0049 0.1988 1.0000
11.500 1.2721 0.02543 0.01777 0.0066 0.1966 1.0000
11.750 1.2837 0.02618 0.01852 0.0081 0.1944 1.0000
12.000 1.2960 0.02701 0.01933 0.0095 0.1924 1.0000
12.250 1.3059 0.02794 0.02040 0.0108 0.1904 1.0000
12.500 1.3155 0.02896 0.02152 0.0119 0.1882 1.0000
12.750 1.3243 0.03007 0.02272 0.0130 0.1859 1.0000
13.000 1.3326 0.03127 0.02398 0.0139 0.1837 1.0000
13.250 1.3411 0.03251 0.02526 0.0146 0.1817 1.0000
13.500 1.3503 0.03375 0.02649 0.0153 0.1796 1.0000
13.750 1.3584 0.03516 0.02794 0.0159 0.1776 1.0000
14.000 1.3620 0.03696 0.02990 0.0162 0.1755 1.0000
14.250 1.3659 0.03882 0.03188 0.0165 0.1734 1.0000
14.500 1.3686 0.04083 0.03399 0.0166 0.1711 1.0000
14.750 1.3717 0.04284 0.03607 0.0166 0.1691 1.0000
15.000 1.3768 0.04471 0.03795 0.0166 0.1670 1.0000
15.250 1.3858 0.04618 0.03938 0.0168 0.1649 1.0000
15.500 1.3795 0.04934 0.04274 0.0161 0.1629 1.0000
15.750 1.3734 0.05260 0.04616 0.0154 0.1605 1.0000
16.000 1.3683 0.05582 0.04951 0.0145 0.1583 1.0000
16.250 1.3643 0.05901 0.05278 0.0136 0.1559 1.0000
16.500 1.3659 0.06159 0.05538 0.0129 0.1539 1.0000
16.750 1.3734 0.06340 0.05716 0.0127 0.1518 1.0000
17.000 1.3528 0.06910 0.06310 0.0103 0.1495 1.0000
17.250 1.3327 0.07495 0.06913 0.0078 0.1468 1.0000
17.500 1.3176 0.08025 0.07456 0.0054 0.1442 1.0000
17.750 1.3144 0.08391 0.07825 0.0039 0.1418 1.0000
18.000 1.3278 0.08502 0.07932 0.0038 0.1397 1.0000
18.250 1.2639 0.09829 0.09293 -0.0029 0.1360 1.0000
18.500 1.2036 0.11168 0.10654 -0.0098 0.1314 1.0000
18.750 1.2177 0.11278 0.10763 -0.0102 0.1295 1.0000
19.000 1.2490 0.11095 0.10573 -0.0089 0.1280 1.0000
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