EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1210 AIRFOIL (e1210-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.45 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1210-il-1000000.txt Download as CSV file: xf-e1210-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1210 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6874 0.08708 0.08437 -0.0517 1.0000 0.0182
-15.000 -0.7008 0.08167 0.07891 -0.0548 1.0000 0.0183
-14.750 -0.7239 0.07507 0.07224 -0.0590 1.0000 0.0183
-14.500 -1.0221 0.03098 0.02741 -0.0941 1.0000 0.0168
-14.250 -1.0289 0.02826 0.02456 -0.0935 1.0000 0.0169
-14.000 -1.0250 0.02649 0.02268 -0.0923 1.0000 0.0171
-13.750 -1.0168 0.02505 0.02116 -0.0909 1.0000 0.0173
-13.500 -1.0056 0.02384 0.01987 -0.0895 1.0000 0.0175
-13.250 -0.9923 0.02279 0.01873 -0.0881 1.0000 0.0178
-13.000 -0.9634 0.02172 0.01758 -0.0894 0.9986 0.0182
-12.750 -0.9272 0.02072 0.01649 -0.0919 0.9958 0.0186
-12.500 -0.8913 0.01926 0.01495 -0.0949 0.9928 0.0193
-12.250 -0.8592 0.01835 0.01399 -0.0964 0.9879 0.0199
-12.000 -0.8233 0.01755 0.01314 -0.0984 0.9826 0.0207
-11.750 -0.7943 0.01693 0.01245 -0.0988 0.9699 0.0214
-11.500 -0.7596 0.01599 0.01145 -0.1006 0.9512 0.0224
-11.250 -0.7014 0.01512 0.01050 -0.1069 0.9271 0.0240
-11.000 -0.6661 0.01460 0.00975 -0.1084 0.8745 0.0253
-10.750 -0.6435 0.01423 0.00921 -0.1073 0.8361 0.0267
-10.500 -0.6198 0.01398 0.00879 -0.1063 0.8064 0.0280
-10.250 -0.5964 0.01356 0.00827 -0.1054 0.7825 0.0298
-10.000 -0.5713 0.01330 0.00790 -0.1047 0.7616 0.0315
-9.500 -0.5202 0.01271 0.00714 -0.1034 0.7251 0.0354
-9.250 -0.4943 0.01240 0.00678 -0.1029 0.7095 0.0373
-9.000 -0.4678 0.01220 0.00649 -0.1023 0.6941 0.0393
-8.500 -0.4143 0.01175 0.00591 -0.1014 0.6654 0.0434
-8.250 -0.3874 0.01154 0.00564 -0.1009 0.6525 0.0456
-8.000 -0.3602 0.01137 0.00541 -0.1005 0.6394 0.0479
-7.750 -0.3327 0.01120 0.00518 -0.1001 0.6279 0.0500
-7.500 -0.3055 0.01103 0.00496 -0.0997 0.6156 0.0523
-7.250 -0.2774 0.01091 0.00478 -0.0993 0.6047 0.0544
-7.000 -0.2501 0.01072 0.00455 -0.0989 0.5939 0.0568
-6.750 -0.2220 0.01060 0.00439 -0.0986 0.5834 0.0591
-6.500 -0.1943 0.01047 0.00420 -0.0983 0.5728 0.0615
-6.250 -0.1662 0.01034 0.00405 -0.0980 0.5631 0.0641
-6.000 -0.1381 0.01029 0.00392 -0.0976 0.5534 0.0664
-5.750 -0.1100 0.01013 0.00377 -0.0974 0.5441 0.0696
-5.500 -0.0819 0.01011 0.00368 -0.0970 0.5342 0.0724
-5.250 -0.0536 0.00997 0.00353 -0.0968 0.5260 0.0755
-5.000 -0.0254 0.00993 0.00344 -0.0965 0.5169 0.0783
-4.750 0.0032 0.00986 0.00333 -0.0962 0.5092 0.0807
-4.500 0.0312 0.00975 0.00321 -0.0959 0.5002 0.0839
-4.250 0.0596 0.00971 0.00313 -0.0957 0.4922 0.0867
-4.000 0.0881 0.00964 0.00302 -0.0954 0.4843 0.0894
-3.750 0.1161 0.00959 0.00294 -0.0951 0.4760 0.0927
-3.500 0.1449 0.00954 0.00288 -0.0949 0.4695 0.0957
-3.250 0.1731 0.00950 0.00279 -0.0946 0.4613 0.0986
-3.000 0.2014 0.00945 0.00273 -0.0944 0.4541 0.1022
-2.750 0.2300 0.00942 0.00268 -0.0942 0.4472 0.1052
-2.500 0.2582 0.00942 0.00261 -0.0939 0.4397 0.1084
-2.250 0.2867 0.00935 0.00256 -0.0937 0.4338 0.1124
-2.000 0.3152 0.00935 0.00253 -0.0935 0.4268 0.1159
-1.750 0.3432 0.00937 0.00249 -0.0932 0.4191 0.1192
-1.500 0.3718 0.00930 0.00245 -0.0930 0.4138 0.1241
-1.250 0.4002 0.00931 0.00243 -0.0928 0.4074 0.1282
-1.000 0.4282 0.00934 0.00241 -0.0925 0.4004 0.1323
-0.750 0.4568 0.00929 0.00240 -0.0924 0.3952 0.1382
-0.500 0.4850 0.00932 0.00239 -0.0921 0.3888 0.1427
-0.250 0.5129 0.00934 0.00240 -0.0919 0.3823 0.1497
0.000 0.5415 0.00932 0.00240 -0.0917 0.3776 0.1566
0.250 0.5696 0.00933 0.00240 -0.0915 0.3716 0.1651
0.500 0.5972 0.00940 0.00244 -0.0912 0.3649 0.1746
0.750 0.6256 0.00936 0.00246 -0.0910 0.3610 0.1895
1.000 0.6537 0.00935 0.00250 -0.0909 0.3560 0.2086
1.250 0.6812 0.00937 0.00255 -0.0906 0.3502 0.2354
1.500 0.7089 0.00936 0.00262 -0.0904 0.3453 0.2715
1.750 0.7367 0.00928 0.00268 -0.0902 0.3409 0.3224
2.000 0.7640 0.00923 0.00276 -0.0900 0.3361 0.3856
2.250 0.7907 0.00919 0.00288 -0.0897 0.3308 0.4646
3.000 0.8654 0.00856 0.00326 -0.0874 0.3193 0.8516
3.250 0.9024 0.00854 0.00339 -0.0889 0.3135 1.0000
3.500 0.9299 0.00865 0.00347 -0.0887 0.3106 1.0000
3.750 0.9573 0.00876 0.00356 -0.0884 0.3073 1.0000
4.000 0.9843 0.00890 0.00366 -0.0880 0.3035 1.0000
4.250 1.0107 0.00908 0.00378 -0.0876 0.2994 1.0000
4.500 1.0371 0.00926 0.00392 -0.0872 0.2955 1.0000
4.750 1.0646 0.00937 0.00402 -0.0870 0.2927 1.0000
5.000 1.0914 0.00951 0.00414 -0.0866 0.2893 1.0000
5.250 1.1178 0.00968 0.00428 -0.0863 0.2858 1.0000
5.500 1.1434 0.00990 0.00445 -0.0858 0.2818 1.0000
5.750 1.1697 0.01007 0.00460 -0.0854 0.2789 1.0000
6.000 1.1966 0.01019 0.00474 -0.0851 0.2765 1.0000
6.250 1.2229 0.01035 0.00488 -0.0847 0.2735 1.0000
6.500 1.2485 0.01054 0.00505 -0.0843 0.2701 1.0000
6.750 1.2732 0.01079 0.00525 -0.0837 0.2662 1.0000
7.000 1.2984 0.01099 0.00545 -0.0832 0.2633 1.0000
7.250 1.3246 0.01113 0.00561 -0.0828 0.2612 1.0000
7.500 1.3501 0.01131 0.00578 -0.0824 0.2586 1.0000
7.750 1.3749 0.01151 0.00598 -0.0818 0.2557 1.0000
8.000 1.3988 0.01176 0.00621 -0.0811 0.2525 1.0000
8.250 1.4211 0.01209 0.00650 -0.0802 0.2487 1.0000
8.500 1.4465 0.01223 0.00667 -0.0798 0.2470 1.0000
8.750 1.4711 0.01241 0.00687 -0.0792 0.2446 1.0000
9.000 1.4946 0.01263 0.00710 -0.0785 0.2421 1.0000
9.250 1.5171 0.01289 0.00735 -0.0777 0.2394 1.0000
9.500 1.5380 0.01321 0.00766 -0.0766 0.2364 1.0000
9.750 1.5581 0.01355 0.00799 -0.0754 0.2335 1.0000
10.000 1.5810 0.01374 0.00822 -0.0746 0.2318 1.0000
10.250 1.6017 0.01395 0.00846 -0.0734 0.2297 1.0000
10.500 1.6203 0.01422 0.00874 -0.0719 0.2274 1.0000
10.750 1.6372 0.01454 0.00907 -0.0701 0.2251 1.0000
11.000 1.6523 0.01493 0.00946 -0.0682 0.2223 1.0000
11.250 1.6654 0.01541 0.00994 -0.0660 0.2193 1.0000
11.500 1.6845 0.01569 0.01026 -0.0647 0.2180 1.0000
11.750 1.7026 0.01600 0.01062 -0.0634 0.2161 1.0000
12.000 1.7191 0.01638 0.01103 -0.0619 0.2138 1.0000
12.250 1.7336 0.01686 0.01152 -0.0602 0.2115 1.0000
12.500 1.7455 0.01746 0.01213 -0.0583 0.2089 1.0000
12.750 1.7530 0.01830 0.01297 -0.0560 0.2058 1.0000
13.000 1.7692 0.01878 0.01352 -0.0548 0.2043 1.0000
13.250 1.7842 0.01935 0.01413 -0.0536 0.2026 1.0000
13.500 1.7973 0.02004 0.01487 -0.0522 0.2006 1.0000
13.750 1.8083 0.02089 0.01575 -0.0508 0.1984 1.0000
14.000 1.8170 0.02193 0.01682 -0.0494 0.1963 1.0000
14.250 1.8222 0.02326 0.01817 -0.0478 0.1937 1.0000
14.500 1.8296 0.02452 0.01948 -0.0466 0.1917 1.0000
14.750 1.8422 0.02548 0.02051 -0.0458 0.1903 1.0000
15.000 1.8529 0.02662 0.02171 -0.0450 0.1886 1.0000
15.250 1.8612 0.02798 0.02311 -0.0442 0.1864 1.0000
15.500 1.8666 0.02961 0.02479 -0.0434 0.1842 1.0000
15.750 1.8686 0.03159 0.02680 -0.0425 0.1820 1.0000
16.000 1.8654 0.03406 0.02930 -0.0417 0.1792 1.0000
16.250 1.8743 0.03556 0.03088 -0.0413 0.1779 1.0000
16.500 1.8820 0.03719 0.03259 -0.0410 0.1760 1.0000
16.750 1.8854 0.03924 0.03470 -0.0406 0.1739 1.0000
17.000 1.8844 0.04177 0.03728 -0.0404 0.1714 1.0000
17.250 1.8788 0.04485 0.04040 -0.0402 0.1689 1.0000
17.500 1.8726 0.04807 0.04367 -0.0402 0.1665 1.0000
17.750 1.8767 0.05030 0.04599 -0.0403 0.1649 1.0000
18.000 1.8783 0.05282 0.04858 -0.0404 0.1627 1.0000
18.250 1.8748 0.05598 0.05180 -0.0408 0.1603 1.0000
18.500 1.8660 0.05983 0.05570 -0.0413 0.1578 1.0000
18.750 1.8518 0.06438 0.06030 -0.0421 0.1547 1.0000
19.000 1.8530 0.06720 0.06321 -0.0427 0.1529 1.0000
19.250 1.8498 0.07058 0.06666 -0.0434 0.1503 1.0000
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Polar data table (+)
Polar graphs
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