EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1213 AIRFOIL (e1213-il) Reynolds number: 50,000 Max Cl/Cd: 22.29 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1213-il-50000-n5.txt Download as CSV file: xf-e1213-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5178 0.11822 0.11014 -0.0090 1.0000 0.1391
-12.500 -0.5028 0.11690 0.10880 -0.0088 1.0000 0.1443
-12.250 -0.5242 0.10971 0.10163 -0.0130 1.0000 0.1506
-12.000 -0.5004 0.10973 0.10163 -0.0116 1.0000 0.1549
-11.750 -0.5057 0.10520 0.09710 -0.0137 1.0000 0.1605
-11.500 -0.5092 0.10100 0.09291 -0.0156 1.0000 0.1657
-11.250 -0.4963 0.09926 0.09115 -0.0155 1.0000 0.1702
-11.000 -0.5340 0.09026 0.08220 -0.0211 1.0000 0.1777
-10.750 -0.5058 0.09081 0.08272 -0.0191 1.0000 0.1809
-10.500 -0.4995 0.08827 0.08018 -0.0197 1.0000 0.1860
-10.250 -0.5400 0.07923 0.07121 -0.0252 1.0000 0.1932
-10.000 -0.5142 0.07952 0.07149 -0.0235 1.0000 0.1966
-9.500 -0.5883 0.06325 0.05531 -0.0331 1.0000 0.2103
-9.250 -0.5687 0.06291 0.05498 -0.0318 1.0000 0.2143
-9.000 -0.6508 0.05304 0.04500 -0.0338 1.0000 0.2212
-8.750 -0.6662 0.04933 0.04116 -0.0329 1.0000 0.2261
-8.500 -0.6444 0.04904 0.04093 -0.0317 1.0000 0.2301
-8.250 -0.6460 0.04667 0.03847 -0.0304 1.0000 0.2355
-8.000 -0.6648 0.04290 0.03438 -0.0285 1.0000 0.2415
-7.750 -0.6452 0.04271 0.03433 -0.0269 1.0000 0.2449
-7.500 -0.6376 0.04193 0.03360 -0.0248 1.0000 0.2489
-7.250 -0.6188 0.03980 0.03120 -0.0266 0.9782 0.2558
-7.000 -0.5796 0.03839 0.02962 -0.0302 0.9499 0.2622
-6.750 -0.5381 0.03745 0.02858 -0.0333 0.9243 0.2683
-6.500 -0.5063 0.03541 0.02604 -0.0363 0.8999 0.2768
-6.250 -0.4672 0.03486 0.02551 -0.0380 0.8765 0.2816
-6.000 -0.4359 0.03409 0.02458 -0.0388 0.8531 0.2873
-5.750 -0.4124 0.03296 0.02307 -0.0388 0.8309 0.2942
-5.500 -0.3861 0.03236 0.02236 -0.0384 0.8103 0.2990
-5.250 -0.3608 0.03189 0.02177 -0.0377 0.7908 0.3039
-5.000 -0.3383 0.03125 0.02089 -0.0369 0.7725 0.3100
-4.750 -0.3162 0.03056 0.01994 -0.0361 0.7554 0.3160
-4.500 -0.2911 0.03022 0.01956 -0.0352 0.7392 0.3207
-4.250 -0.2669 0.02977 0.01895 -0.0344 0.7245 0.3264
-4.000 -0.2443 0.02923 0.01815 -0.0336 0.7088 0.3332
-3.750 -0.2194 0.02890 0.01780 -0.0328 0.6940 0.3383
-3.500 -0.1944 0.02858 0.01738 -0.0321 0.6807 0.3441
-3.250 -0.1700 0.02819 0.01680 -0.0314 0.6675 0.3509
-3.000 -0.1450 0.02789 0.01644 -0.0308 0.6539 0.3569
-2.750 -0.1193 0.02764 0.01612 -0.0300 0.6422 0.3634
-2.500 -0.0942 0.02737 0.01570 -0.0295 0.6295 0.3709
-2.250 -0.0685 0.02715 0.01545 -0.0289 0.6175 0.3775
-2.000 -0.0421 0.02694 0.01518 -0.0283 0.6067 0.3851
-1.750 -0.0162 0.02679 0.01492 -0.0280 0.5944 0.3939
-1.500 0.0111 0.02659 0.01470 -0.0274 0.5849 0.4017
-1.250 0.0371 0.02652 0.01459 -0.0271 0.5728 0.4113
-1.000 0.0644 0.02638 0.01443 -0.0267 0.5633 0.4206
-0.750 0.0906 0.02634 0.01435 -0.0263 0.5520 0.4322
-0.500 0.1171 0.02625 0.01428 -0.0258 0.5430 0.4431
-0.250 0.1428 0.02624 0.01429 -0.0253 0.5324 0.4562
0.000 0.1689 0.02617 0.01420 -0.0247 0.5237 0.4711
0.250 0.1938 0.02620 0.01435 -0.0241 0.5135 0.4870
0.500 0.2198 0.02612 0.01426 -0.0233 0.5059 0.5062
0.750 0.2435 0.02622 0.01454 -0.0226 0.4954 0.5276
1.000 0.2691 0.02612 0.01446 -0.0217 0.4882 0.5547
1.250 0.2913 0.02627 0.01488 -0.0207 0.4784 0.5849
1.500 0.3155 0.02620 0.01494 -0.0195 0.4710 0.6242
1.750 0.3380 0.02630 0.01530 -0.0182 0.4623 0.6724
2.000 0.3633 0.02632 0.01558 -0.0170 0.4542 0.7342
2.250 0.3994 0.02641 0.01586 -0.0175 0.4462 0.8119
2.500 0.4510 0.02672 0.01627 -0.0214 0.4355 0.8941
2.750 0.5054 0.02708 0.01655 -0.0263 0.4262 0.9620
3.000 0.5480 0.02751 0.01690 -0.0295 0.4170 1.0000
3.250 0.5689 0.02773 0.01687 -0.0283 0.4116 1.0000
3.500 0.5834 0.02854 0.01773 -0.0269 0.4031 1.0000
3.750 0.6037 0.02893 0.01799 -0.0257 0.3970 1.0000
4.000 0.6239 0.02940 0.01834 -0.0245 0.3912 1.0000
4.250 0.6394 0.03025 0.01923 -0.0232 0.3835 1.0000
4.500 0.6614 0.03062 0.01947 -0.0221 0.3779 1.0000
4.750 0.6802 0.03131 0.02013 -0.0209 0.3720 1.0000
5.000 0.6953 0.03228 0.02115 -0.0196 0.3649 1.0000
5.250 0.7178 0.03269 0.02146 -0.0186 0.3598 1.0000
5.500 0.7365 0.03346 0.02219 -0.0175 0.3544 1.0000
5.750 0.7481 0.03476 0.02359 -0.0161 0.3476 1.0000
6.000 0.7694 0.03532 0.02410 -0.0151 0.3427 1.0000
6.250 0.7946 0.03565 0.02429 -0.0144 0.3387 1.0000
6.500 0.7948 0.03779 0.02667 -0.0125 0.3315 1.0000
6.750 0.8112 0.03873 0.02761 -0.0114 0.3265 1.0000
7.000 0.8372 0.03902 0.02780 -0.0107 0.3229 1.0000
7.250 0.8353 0.04136 0.03031 -0.0088 0.3172 1.0000
7.500 0.8316 0.04374 0.03281 -0.0070 0.3114 1.0000
7.750 0.8503 0.04450 0.03353 -0.0061 0.3075 1.0000
8.000 0.8835 0.04433 0.03325 -0.0057 0.3046 1.0000
8.250 0.7624 0.05581 0.04513 -0.0027 0.2942 1.0000
8.500 0.7692 0.05786 0.04717 -0.0023 0.2903 1.0000
8.750 0.8005 0.05739 0.04666 -0.0011 0.2882 1.0000
9.250 0.7117 0.07497 0.06438 -0.0070 0.2715 1.0000
9.750 0.6555 0.09008 0.07956 -0.0128 0.2584 1.0000
10.000 0.6724 0.09136 0.08084 -0.0124 0.2558 1.0000
10.250 0.6959 0.09176 0.08121 -0.0114 0.2540 1.0000
10.750 0.6479 0.10611 0.09566 -0.0175 0.2432 1.0000
11.000 0.6610 0.10809 0.09765 -0.0175 0.2405 1.0000
11.250 0.6817 0.10904 0.09862 -0.0168 0.2385 1.0000
11.500 0.6556 0.11654 0.10616 -0.0204 0.2334 1.0000
11.750 0.6526 0.12092 0.11058 -0.0220 0.2303 1.0000
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Polar data table (+)
Polar graphs
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