EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E1212 AIRFOIL (e1212-il) Reynolds number: 50,000 Max Cl/Cd: 7.07 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1212-il-50000.txt Download as CSV file: xf-e1212-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E1212 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3088 0.13103 0.12349 -0.0128 1.0000 0.3088
-10.750 -0.2585 0.12249 0.11488 -0.0122 1.0000 0.3183
-10.500 -0.2818 0.12372 0.11619 -0.0128 1.0000 0.3283
-10.250 -0.2492 0.11719 0.10964 -0.0128 1.0000 0.3352
-10.000 -0.2527 0.11623 0.10874 -0.0128 1.0000 0.3477
-9.750 -0.2415 0.11231 0.10485 -0.0131 1.0000 0.3540
-9.500 -0.2296 0.10980 0.10238 -0.0128 1.0000 0.3663
-9.250 -0.2324 0.10757 0.10022 -0.0129 1.0000 0.3740
-9.000 -0.2132 0.10442 0.09709 -0.0126 1.0000 0.3860
-8.750 -0.2197 0.10270 0.09547 -0.0123 1.0000 0.3951
-8.500 -0.2009 0.09975 0.09256 -0.0119 1.0000 0.4080
-8.250 -0.2038 0.09776 0.09067 -0.0113 1.0000 0.4171
-8.000 -0.1947 0.09589 0.08889 -0.0105 1.0000 0.4315
-7.750 -0.1868 0.09310 0.08621 -0.0099 1.0000 0.4403
-7.500 -0.2027 0.09343 0.08674 -0.0075 1.0000 0.4550
-7.250 -0.1840 0.08999 0.08344 -0.0067 1.0000 0.4633
-7.000 -0.2200 0.09209 0.08583 0.0002 1.0000 0.4682
-6.750 -0.2823 0.09637 0.09032 0.0045 0.9933 0.4775
-6.500 -0.2347 0.09211 0.08598 -0.0031 0.9771 0.4991
-6.250 -0.1752 0.08680 0.08056 -0.0107 0.9613 0.5213
-6.000 -0.1145 0.08172 0.07538 -0.0184 0.9459 0.5440
-5.750 -0.0444 0.07642 0.06995 -0.0272 0.9330 0.5693
-5.500 0.0157 0.07211 0.06553 -0.0350 0.9181 0.5962
-5.250 0.0367 0.07096 0.06430 -0.0379 0.9001 0.6263
-5.000 -0.1080 0.06447 0.05770 -0.0479 0.8737 0.4327
-4.750 -0.1091 0.05895 0.05199 -0.0547 0.8586 0.4072
-4.500 -0.1065 0.05571 0.04862 -0.0573 0.8421 0.4032
-4.250 -0.1093 0.05274 0.04548 -0.0592 0.8257 0.4007
-4.000 -0.0984 0.05050 0.04307 -0.0605 0.8109 0.4033
-3.750 -0.0749 0.04780 0.04011 -0.0635 0.7991 0.4077
-3.500 -0.0704 0.04619 0.03827 -0.0638 0.7835 0.4108
-3.250 -0.0542 0.04489 0.03680 -0.0639 0.7700 0.4157
-3.000 -0.0220 0.04390 0.03575 -0.0640 0.7585 0.4227
-2.750 -0.0123 0.04336 0.03508 -0.0632 0.7440 0.4276
-2.500 0.0143 0.04196 0.03331 -0.0647 0.7335 0.4353
-2.250 0.0312 0.04182 0.03323 -0.0631 0.7200 0.4408
-2.000 0.0502 0.04157 0.03289 -0.0624 0.7082 0.4474
-1.750 0.0758 0.04084 0.03185 -0.0632 0.6973 0.4560
-1.500 0.0896 0.04108 0.03217 -0.0615 0.6850 0.4621
-1.250 0.1196 0.04054 0.03150 -0.0615 0.6753 0.4713
-1.000 0.1304 0.04104 0.03186 -0.0609 0.6632 0.4785
-0.750 0.1603 0.04066 0.03150 -0.0602 0.6542 0.4884
-0.500 0.1687 0.04155 0.03230 -0.0593 0.6423 0.4968
-0.250 0.1985 0.04125 0.03198 -0.0589 0.6336 0.5074
0.000 0.2053 0.04246 0.03317 -0.0578 0.6228 0.5167
0.250 0.2321 0.04246 0.03316 -0.0573 0.6138 0.5295
0.500 0.2426 0.04363 0.03426 -0.0565 0.6043 0.5418
0.750 0.2540 0.04461 0.03534 -0.0552 0.5950 0.5531
1.000 0.3001 0.04365 0.03431 -0.0552 0.5888 0.5770
1.250 0.2696 0.04751 0.03825 -0.0532 0.5772 0.5816
1.500 0.3126 0.04677 0.03757 -0.0530 0.5706 0.6108
1.750 0.2864 0.05053 0.04142 -0.0511 0.5621 0.6187
2.000 0.2857 0.05240 0.04338 -0.0496 0.5546 0.6390
2.250 0.3528 0.04991 0.04120 -0.0489 0.5485 0.7127
2.500 0.2905 0.05610 0.04744 -0.0469 0.5432 0.7051
2.750 0.2780 0.05865 0.05028 -0.0452 0.5386 0.7478
3.000 0.3813 0.05735 0.04906 -0.0534 0.5269 1.0000
3.250 0.1888 0.07105 0.06294 -0.0494 0.6170 0.7488
3.500 0.2524 0.07367 0.06569 -0.0572 0.6108 1.0000
3.750 0.2813 0.07502 0.06669 -0.0575 0.5900 1.0000
4.000 0.3329 0.07242 0.06367 -0.0542 0.5311 1.0000
4.250 0.3613 0.07485 0.06593 -0.0549 0.5274 1.0000
4.500 0.2460 0.08349 0.07493 -0.0584 0.6355 1.0000
4.750 0.2803 0.08756 0.07882 -0.0604 0.6299 1.0000
5.000 0.2701 0.08764 0.07882 -0.0583 0.6169 1.0000
5.250 0.3116 0.09197 0.08299 -0.0606 0.6106 1.0000
5.500 0.2957 0.09203 0.08299 -0.0583 0.5984 1.0000
5.750 0.3331 0.09587 0.08671 -0.0600 0.5906 1.0000
6.000 0.3221 0.09666 0.08745 -0.0585 0.5807 1.0000
6.250 0.3450 0.09941 0.09011 -0.0591 0.5725 1.0000
6.500 0.3772 0.10401 0.09460 -0.0606 0.5681 1.0000
6.750 0.3624 0.10365 0.09422 -0.0588 0.5551 1.0000
7.000 0.4017 0.10827 0.09876 -0.0604 0.5491 1.0000
7.250 0.3838 0.10841 0.09887 -0.0589 0.5391 1.0000
7.500 0.4056 0.11132 0.10172 -0.0594 0.5319 1.0000
8.000 0.3420 0.11846 0.10969 -0.0516 0.5061 1.0000
8.250 0.3388 0.11946 0.11069 -0.0510 0.4949 1.0000
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Polar data table (+)
Polar graphs
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