EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 1200 AIRFOIL (e1200-il) Reynolds number: 50,000 Max Cl/Cd: 9.29 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1200-il-50000.txt Download as CSV file: xf-e1200-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1200 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3614 0.11633 0.11122 -0.0032 1.0000 0.3615
-7.000 -0.6856 0.08002 0.07414 -0.0299 1.0000 0.1515
-6.750 -0.7087 0.07172 0.06511 -0.0320 1.0000 0.1376
-6.500 -0.7025 0.06773 0.06099 -0.0314 1.0000 0.1360
-6.250 -0.6958 0.06362 0.05661 -0.0312 1.0000 0.1338
-6.000 -0.6867 0.05933 0.05189 -0.0314 1.0000 0.1308
-5.750 -0.6735 0.05503 0.04697 -0.0317 1.0000 0.1276
-5.500 -0.6563 0.05152 0.04282 -0.0319 1.0000 0.1259
-5.250 -0.6373 0.04887 0.03976 -0.0316 1.0000 0.1262
-5.000 -0.6181 0.04691 0.03757 -0.0312 1.0000 0.1287
-4.750 -0.5979 0.04516 0.03553 -0.0308 1.0000 0.1330
-4.500 -0.5760 0.04350 0.03342 -0.0303 1.0000 0.1368
-4.250 -0.5546 0.04182 0.03156 -0.0296 1.0000 0.1408
-4.000 -0.5341 0.04063 0.03035 -0.0287 1.0000 0.1474
-3.750 -0.5132 0.03956 0.02917 -0.0278 1.0000 0.1575
-3.500 -0.4927 0.03867 0.02827 -0.0265 1.0000 0.1716
-3.250 -0.4736 0.03773 0.02758 -0.0250 1.0000 0.1928
-3.000 -0.4541 0.03656 0.02675 -0.0237 1.0000 0.2378
-2.750 -0.4359 0.03371 0.02605 -0.0228 1.0000 0.4345
-2.500 -0.4473 0.03539 0.02884 -0.0105 1.0000 0.6742
-2.250 -0.4538 0.03690 0.03031 -0.0004 1.0000 0.7399
-2.000 -0.4584 0.03780 0.03112 0.0085 1.0000 0.7863
-1.750 -0.4624 0.03829 0.03152 0.0170 1.0000 0.8249
-1.500 -0.4627 0.03857 0.03167 0.0242 1.0000 0.8640
-1.250 -0.4485 0.03915 0.03207 0.0290 1.0000 0.9059
-1.000 -0.2075 0.04658 0.03845 -0.0076 1.0000 0.9854
-0.750 -0.1521 0.04767 0.03924 -0.0158 1.0000 1.0000
-0.500 -0.1509 0.04733 0.03880 -0.0138 1.0000 1.0000
-0.250 -0.1498 0.04699 0.03837 -0.0118 1.0000 1.0000
0.000 -0.1488 0.04667 0.03796 -0.0097 1.0000 1.0000
0.250 -0.1479 0.04635 0.03756 -0.0076 1.0000 1.0000
0.500 -0.1473 0.04602 0.03716 -0.0054 1.0000 1.0000
0.750 -0.1468 0.04568 0.03675 -0.0032 1.0000 1.0000
1.000 -0.1463 0.04534 0.03634 -0.0011 1.0000 1.0000
1.250 -0.1457 0.04499 0.03594 0.0010 1.0000 1.0000
1.500 -0.1445 0.04468 0.03558 0.0030 1.0000 1.0000
1.750 -0.1415 0.04449 0.03532 0.0046 1.0000 1.0000
2.000 -0.1342 0.04458 0.03534 0.0054 1.0000 1.0000
2.250 -0.1226 0.04499 0.03568 0.0054 1.0000 1.0000
2.500 -0.0905 0.04706 0.03764 0.0015 0.9936 1.0000
2.750 -0.0516 0.04970 0.04015 -0.0037 0.9824 1.0000
3.000 -0.0142 0.05220 0.04255 -0.0084 0.9692 1.0000
3.250 0.0168 0.05401 0.04430 -0.0120 0.9543 1.0000
3.500 0.0464 0.05569 0.04593 -0.0152 0.9367 1.0000
3.750 0.0773 0.05762 0.04780 -0.0184 0.9187 1.0000
4.000 0.1094 0.05968 0.04982 -0.0218 0.8996 1.0000
4.250 0.1438 0.06196 0.05205 -0.0254 0.8800 1.0000
4.500 0.1854 0.06492 0.05496 -0.0299 0.8599 1.0000
4.750 0.2063 0.06629 0.05632 -0.0312 0.8393 1.0000
5.000 0.2533 0.06868 0.05867 -0.0353 0.8081 1.0000
5.250 0.3403 0.06647 0.05633 -0.0381 0.7161 1.0000
5.500 0.3879 0.06731 0.05715 -0.0408 0.6950 1.0000
5.750 0.4165 0.06815 0.05798 -0.0418 0.6753 1.0000
6.000 0.4389 0.06911 0.05896 -0.0423 0.6566 1.0000
6.250 0.4658 0.07005 0.05991 -0.0431 0.6389 1.0000
6.500 0.4944 0.07088 0.06076 -0.0440 0.6217 1.0000
6.750 0.5215 0.07181 0.06172 -0.0447 0.6057 1.0000
7.000 0.5487 0.07264 0.06259 -0.0454 0.5897 1.0000
7.250 0.5741 0.07356 0.06354 -0.0458 0.5742 1.0000
7.500 0.5981 0.07454 0.06456 -0.0462 0.5591 1.0000
7.750 0.6214 0.07555 0.06561 -0.0464 0.5444 1.0000
8.000 0.6452 0.07655 0.06667 -0.0467 0.5306 1.0000
8.250 0.6764 0.07690 0.06706 -0.0469 0.5177 1.0000
8.500 0.7125 0.07670 0.06694 -0.0472 0.5056 1.0000
8.750 0.7182 0.07919 0.06948 -0.0469 0.4912 1.0000
9.000 0.7225 0.08198 0.07232 -0.0468 0.4775 1.0000
9.250 0.7300 0.08468 0.07506 -0.0469 0.4652 1.0000
9.500 0.7704 0.08393 0.07441 -0.0467 0.4551 1.0000
9.750 0.7779 0.08659 0.07713 -0.0467 0.4428 1.0000
10.000 0.7592 0.09251 0.08308 -0.0473 0.4313 1.0000
10.250 0.7827 0.09370 0.08434 -0.0472 0.4215 1.0000
10.500 0.7871 0.09708 0.08778 -0.0476 0.4112 1.0000
10.750 0.7728 0.10297 0.09373 -0.0487 0.4029 1.0000
11.000 0.8104 0.10252 0.09338 -0.0481 0.3932 1.0000
11.250 0.7739 0.11131 0.10218 -0.0504 0.3869 1.0000
11.500 0.7809 0.11484 0.10578 -0.0511 0.3794 1.0000
11.750 0.7857 0.11894 0.10994 -0.0521 0.3736 1.0000
12.000 0.7666 0.12577 0.11681 -0.0544 0.3712 1.0000
12.250 0.7575 0.13149 0.12259 -0.0564 0.3699 1.0000
12.500 0.7575 0.13703 0.12819 -0.0585 0.3731 1.0000
12.750 0.7706 0.14207 0.13333 -0.0604 0.3763 1.0000
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Polar data table (+)
Polar graphs
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