EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1210 AIRFOIL (e1210-il) Reynolds number: 500,000 Max Cl/Cd: 93.21 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1210-il-500000-n5.txt Download as CSV file: xf-e1210-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5862 0.08952 0.08633 -0.0484 1.0000 0.0199
-14.000 -0.6071 0.08275 0.07950 -0.0523 1.0000 0.0201
-13.750 -0.6378 0.07497 0.07165 -0.0571 1.0000 0.0203
-13.500 -0.6917 0.06454 0.06112 -0.0641 1.0000 0.0200
-13.250 -0.9143 0.03135 0.02715 -0.0889 1.0000 0.0184
-13.000 -0.9071 0.02865 0.02429 -0.0901 0.9983 0.0187
-12.750 -0.8807 0.02635 0.02186 -0.0935 0.9918 0.0192
-12.250 -0.8341 0.02345 0.01875 -0.0954 0.9644 0.0203
-12.000 -0.7947 0.02215 0.01730 -0.0990 0.9411 0.0211
-11.750 -0.7381 0.02066 0.01567 -0.1059 0.9135 0.0222
-11.500 -0.6994 0.01971 0.01448 -0.1088 0.8674 0.0233
-11.250 -0.6770 0.01914 0.01368 -0.1081 0.8301 0.0243
-11.000 -0.6559 0.01858 0.01294 -0.1071 0.8013 0.0252
-10.750 -0.6341 0.01803 0.01225 -0.1062 0.7778 0.0263
-10.500 -0.6112 0.01756 0.01163 -0.1054 0.7575 0.0276
-10.250 -0.5880 0.01708 0.01102 -0.1047 0.7387 0.0290
-10.000 -0.5641 0.01665 0.01047 -0.1040 0.7216 0.0305
-9.750 -0.5394 0.01625 0.00996 -0.1033 0.7059 0.0321
-9.500 -0.5147 0.01585 0.00947 -0.1027 0.6913 0.0339
-9.250 -0.4894 0.01553 0.00902 -0.1021 0.6769 0.0357
-9.000 -0.4638 0.01516 0.00859 -0.1016 0.6634 0.0375
-8.750 -0.4379 0.01487 0.00819 -0.1011 0.6507 0.0394
-8.500 -0.4120 0.01457 0.00781 -0.1006 0.6380 0.0412
-8.250 -0.3854 0.01429 0.00746 -0.1001 0.6264 0.0432
-8.000 -0.3591 0.01405 0.00713 -0.0996 0.6150 0.0452
-7.750 -0.3322 0.01380 0.00682 -0.0992 0.6035 0.0475
-7.500 -0.3054 0.01360 0.00653 -0.0988 0.5928 0.0497
-7.250 -0.2783 0.01338 0.00626 -0.0984 0.5820 0.0521
-7.000 -0.2511 0.01321 0.00600 -0.0979 0.5721 0.0545
-6.750 -0.2238 0.01301 0.00577 -0.0976 0.5620 0.0571
-6.500 -0.1964 0.01287 0.00554 -0.0972 0.5525 0.0600
-6.250 -0.1689 0.01270 0.00536 -0.0968 0.5428 0.0629
-6.000 -0.1414 0.01259 0.00516 -0.0965 0.5341 0.0658
-5.750 -0.1136 0.01243 0.00497 -0.0961 0.5251 0.0682
-5.500 -0.0861 0.01232 0.00479 -0.0958 0.5160 0.0709
-5.250 -0.0581 0.01220 0.00461 -0.0954 0.5081 0.0735
-5.000 -0.0304 0.01208 0.00447 -0.0951 0.4996 0.0761
-4.750 -0.0025 0.01200 0.00432 -0.0948 0.4919 0.0789
-4.500 0.0254 0.01189 0.00417 -0.0945 0.4833 0.0816
-4.250 0.0531 0.01182 0.00406 -0.0941 0.4757 0.0845
-4.000 0.0813 0.01174 0.00393 -0.0938 0.4689 0.0874
-3.750 0.1092 0.01166 0.00382 -0.0935 0.4612 0.0902
-3.500 0.1371 0.01160 0.00373 -0.0932 0.4541 0.0933
-3.250 0.1652 0.01156 0.00363 -0.0929 0.4466 0.0964
-3.000 0.1930 0.01150 0.00354 -0.0926 0.4396 0.0994
-2.750 0.2211 0.01145 0.00347 -0.0923 0.4338 0.1027
-2.500 0.2493 0.01142 0.00340 -0.0921 0.4271 0.1061
-2.250 0.2769 0.01140 0.00334 -0.0917 0.4202 0.1094
-2.000 0.3051 0.01136 0.00329 -0.0915 0.4141 0.1133
-1.750 0.3331 0.01135 0.00324 -0.0912 0.4076 0.1169
-1.500 0.3608 0.01134 0.00320 -0.0909 0.4017 0.1209
-1.250 0.3889 0.01131 0.00318 -0.0906 0.3963 0.1252
-1.000 0.4169 0.01132 0.00315 -0.0904 0.3901 0.1293
-0.750 0.4444 0.01133 0.00314 -0.0901 0.3838 0.1343
-0.500 0.4724 0.01133 0.00314 -0.0898 0.3787 0.1395
-0.250 0.5004 0.01134 0.00313 -0.0895 0.3733 0.1447
0.000 0.5279 0.01136 0.00315 -0.0892 0.3676 0.1517
0.250 0.5556 0.01140 0.00317 -0.0890 0.3624 0.1584
0.500 0.5834 0.01140 0.00319 -0.0887 0.3571 0.1677
0.750 0.6109 0.01144 0.00323 -0.0884 0.3520 0.1775
1.000 0.6381 0.01150 0.00328 -0.0881 0.3470 0.1904
1.250 0.6658 0.01150 0.00334 -0.0879 0.3426 0.2073
1.500 0.6933 0.01152 0.00340 -0.0876 0.3375 0.2277
1.750 0.7202 0.01156 0.00348 -0.0873 0.3327 0.2545
2.000 0.7472 0.01157 0.00358 -0.0870 0.3288 0.2911
2.250 0.7745 0.01155 0.00367 -0.0867 0.3248 0.3360
2.500 0.8013 0.01151 0.00378 -0.0864 0.3203 0.3948
2.750 0.8275 0.01148 0.00392 -0.0861 0.3158 0.4688
3.000 0.8532 0.01142 0.00408 -0.0856 0.3119 0.5579
3.250 0.8785 0.01126 0.00423 -0.0850 0.3087 0.6720
3.500 0.9001 0.01103 0.00440 -0.0834 0.3052 0.8098
3.750 0.9356 0.01095 0.00453 -0.0846 0.3010 1.0000
4.000 0.9614 0.01116 0.00467 -0.0841 0.2970 1.0000
4.250 0.9879 0.01131 0.00480 -0.0837 0.2938 1.0000
4.500 1.0143 0.01148 0.00494 -0.0833 0.2903 1.0000
4.750 1.0403 0.01166 0.00510 -0.0829 0.2868 1.0000
5.000 1.0659 0.01187 0.00526 -0.0824 0.2835 1.0000
5.250 1.0909 0.01211 0.00546 -0.0818 0.2803 1.0000
5.500 1.1170 0.01228 0.00562 -0.0814 0.2776 1.0000
5.750 1.1427 0.01247 0.00580 -0.0809 0.2744 1.0000
6.000 1.1678 0.01268 0.00600 -0.0804 0.2710 1.0000
6.250 1.1924 0.01292 0.00620 -0.0798 0.2677 1.0000
6.500 1.2163 0.01319 0.00644 -0.0791 0.2647 1.0000
6.750 1.2412 0.01339 0.00666 -0.0785 0.2624 1.0000
7.000 1.2659 0.01361 0.00687 -0.0779 0.2598 1.0000
7.250 1.2900 0.01384 0.00711 -0.0773 0.2569 1.0000
7.500 1.3133 0.01410 0.00737 -0.0765 0.2539 1.0000
7.750 1.3357 0.01440 0.00764 -0.0756 0.2509 1.0000
8.000 1.3578 0.01470 0.00793 -0.0747 0.2482 1.0000
8.250 1.3810 0.01494 0.00820 -0.0740 0.2459 1.0000
8.500 1.4034 0.01520 0.00848 -0.0731 0.2435 1.0000
8.750 1.4248 0.01549 0.00878 -0.0721 0.2409 1.0000
9.000 1.4445 0.01581 0.00911 -0.0708 0.2384 1.0000
9.250 1.4618 0.01616 0.00945 -0.0691 0.2359 1.0000
9.500 1.4784 0.01654 0.00983 -0.0674 0.2335 1.0000
9.750 1.4974 0.01684 0.01018 -0.0660 0.2313 1.0000
10.000 1.5152 0.01719 0.01056 -0.0645 0.2291 1.0000
10.250 1.5322 0.01758 0.01098 -0.0630 0.2269 1.0000
10.500 1.5479 0.01803 0.01145 -0.0614 0.2246 1.0000
10.750 1.5623 0.01854 0.01197 -0.0596 0.2224 1.0000
11.000 1.5750 0.01915 0.01258 -0.0578 0.2201 1.0000
11.250 1.5902 0.01967 0.01316 -0.0563 0.2183 1.0000
11.500 1.6054 0.02022 0.01377 -0.0549 0.2163 1.0000
11.750 1.6193 0.02086 0.01445 -0.0535 0.2142 1.0000
12.000 1.6319 0.02159 0.01523 -0.0521 0.2120 1.0000
12.250 1.6430 0.02244 0.01611 -0.0507 0.2098 1.0000
12.500 1.6524 0.02345 0.01714 -0.0492 0.2077 1.0000
12.750 1.6606 0.02460 0.01832 -0.0478 0.2055 1.0000
13.000 1.6733 0.02552 0.01931 -0.0469 0.2038 1.0000
13.250 1.6844 0.02658 0.02044 -0.0460 0.2015 1.0000
13.500 1.6939 0.02780 0.02172 -0.0450 0.1994 1.0000
13.750 1.7016 0.02921 0.02317 -0.0441 0.1970 1.0000
14.000 1.7068 0.03086 0.02486 -0.0433 0.1946 1.0000
14.250 1.7104 0.03271 0.02674 -0.0425 0.1924 1.0000
14.500 1.7190 0.03420 0.02831 -0.0420 0.1905 1.0000
14.750 1.7260 0.03586 0.03005 -0.0415 0.1884 1.0000
15.000 1.7308 0.03776 0.03202 -0.0411 0.1860 1.0000
15.250 1.7333 0.03992 0.03424 -0.0407 0.1837 1.0000
15.500 1.7339 0.04230 0.03666 -0.0404 0.1816 1.0000
15.750 1.7324 0.04494 0.03935 -0.0402 0.1795 1.0000
16.000 1.7366 0.04710 0.04160 -0.0401 0.1777 1.0000
16.250 1.7391 0.04949 0.04408 -0.0401 0.1756 1.0000
16.500 1.7400 0.05210 0.04677 -0.0403 0.1735 1.0000
16.750 1.7382 0.05509 0.04982 -0.0405 0.1710 1.0000
17.000 1.7335 0.05845 0.05324 -0.0410 0.1685 1.0000
17.250 1.7291 0.06187 0.05671 -0.0415 0.1662 1.0000
17.500 1.7292 0.06484 0.05978 -0.0420 0.1641 1.0000
17.750 1.7275 0.06806 0.06309 -0.0427 0.1617 1.0000
18.000 1.7217 0.07187 0.06697 -0.0436 0.1590 1.0000
18.250 1.7133 0.07608 0.07123 -0.0447 0.1564 1.0000
18.500 1.7073 0.08004 0.07527 -0.0458 0.1539 1.0000
18.750 1.7029 0.08389 0.07921 -0.0469 0.1510 1.0000
19.000 1.6950 0.08824 0.08365 -0.0483 0.1481 1.0000
19.250 1.6842 0.09308 0.08853 -0.0500 0.1451 1.0000
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Polar data table (+)
Polar graphs
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