EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il) Reynolds number: 100,000 Max Cl/Cd: 39.72 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1212mod-il-100000-n5.txt Download as CSV file: xf-e1212mod-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E1212MOD AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7953 0.04472 0.03866 -0.0644 1.0000 0.1008
-11.250 -0.8304 0.03981 0.03354 -0.0656 1.0000 0.1021
-11.000 -0.8488 0.03712 0.03065 -0.0634 1.0000 0.1044
-10.750 -0.8386 0.03654 0.03010 -0.0621 1.0000 0.1071
-10.500 -0.8341 0.03527 0.02871 -0.0605 1.0000 0.1105
-10.250 -0.8299 0.03377 0.02703 -0.0588 1.0000 0.1141
-10.000 -0.8150 0.03336 0.02665 -0.0574 1.0000 0.1168
-9.750 -0.8049 0.03241 0.02557 -0.0558 1.0000 0.1206
-9.500 -0.7957 0.03139 0.02440 -0.0540 1.0000 0.1242
-9.250 -0.7704 0.03105 0.02409 -0.0542 0.9879 0.1276
-9.000 -0.7375 0.02982 0.02252 -0.0567 0.9503 0.1335
-8.750 -0.6968 0.02954 0.02225 -0.0594 0.9167 0.1379
-8.500 -0.6603 0.02884 0.02127 -0.0618 0.8847 0.1440
-8.250 -0.6286 0.02837 0.02064 -0.0627 0.8562 0.1488
-8.000 -0.6004 0.02818 0.02033 -0.0628 0.8321 0.1533
-7.750 -0.5790 0.02749 0.01926 -0.0620 0.8110 0.1584
-7.500 -0.5548 0.02708 0.01876 -0.0614 0.7918 0.1619
-7.250 -0.5301 0.02681 0.01842 -0.0606 0.7738 0.1654
-7.000 -0.5072 0.02635 0.01775 -0.0597 0.7570 0.1692
-6.750 -0.4854 0.02573 0.01680 -0.0588 0.7405 0.1734
-6.500 -0.4609 0.02531 0.01636 -0.0581 0.7238 0.1767
-6.250 -0.4360 0.02504 0.01605 -0.0574 0.7075 0.1803
-6.000 -0.4117 0.02468 0.01552 -0.0566 0.6923 0.1847
-5.750 -0.3880 0.02420 0.01474 -0.0559 0.6771 0.1891
-5.500 -0.3626 0.02378 0.01433 -0.0553 0.6616 0.1924
-5.250 -0.3371 0.02345 0.01395 -0.0546 0.6478 0.1956
-5.000 -0.3118 0.02307 0.01343 -0.0540 0.6350 0.1990
-4.750 -0.2862 0.02266 0.01286 -0.0534 0.6224 0.2026
-4.500 -0.2607 0.02225 0.01217 -0.0528 0.6119 0.2059
-4.250 -0.2345 0.02188 0.01183 -0.0523 0.6006 0.2086
-3.750 -0.1821 0.02134 0.01114 -0.0512 0.5814 0.2152
-3.500 -0.1557 0.02107 0.01071 -0.0506 0.5728 0.2190
-3.250 -0.1290 0.02080 0.01028 -0.0501 0.5644 0.2225
-3.000 -0.1027 0.02057 0.01007 -0.0496 0.5556 0.2258
-2.750 -0.0764 0.02043 0.00984 -0.0490 0.5483 0.2298
-2.500 -0.0497 0.02027 0.00965 -0.0486 0.5399 0.2347
-2.000 0.0035 0.02000 0.00924 -0.0475 0.5249 0.2442
-1.750 0.0301 0.01989 0.00915 -0.0471 0.5167 0.2498
-1.500 0.0569 0.01981 0.00895 -0.0465 0.5093 0.2570
-1.250 0.0833 0.01976 0.00890 -0.0460 0.5022 0.2637
-1.000 0.1100 0.01970 0.00883 -0.0455 0.4941 0.2728
-0.750 0.1365 0.01964 0.00874 -0.0450 0.4871 0.2814
-0.500 0.1631 0.01962 0.00866 -0.0445 0.4801 0.2919
-0.250 0.1893 0.01955 0.00865 -0.0439 0.4720 0.3019
0.000 0.2160 0.01954 0.00855 -0.0434 0.4652 0.3143
0.250 0.2420 0.01949 0.00857 -0.0428 0.4585 0.3256
0.500 0.2683 0.01948 0.00859 -0.0423 0.4507 0.3384
0.750 0.2945 0.01945 0.00858 -0.0417 0.4441 0.3512
1.000 0.3208 0.01946 0.00861 -0.0412 0.4377 0.3638
1.250 0.3470 0.01948 0.00868 -0.0406 0.4300 0.3779
1.500 0.3730 0.01946 0.00870 -0.0400 0.4236 0.3924
1.750 0.3991 0.01948 0.00876 -0.0395 0.4171 0.4083
2.000 0.4252 0.01951 0.00887 -0.0389 0.4098 0.4257
2.250 0.4516 0.01951 0.00888 -0.0384 0.4039 0.4456
2.500 0.4778 0.01953 0.00898 -0.0379 0.3981 0.4689
2.750 0.5033 0.01954 0.00915 -0.0373 0.3918 0.4989
3.000 0.5279 0.01945 0.00927 -0.0364 0.3865 0.5479
3.250 0.5508 0.01924 0.00938 -0.0350 0.3822 0.6377
3.500 0.5804 0.01903 0.00977 -0.0345 0.3758 0.8039
3.750 0.6571 0.01914 0.00996 -0.0434 0.3678 0.9924
4.000 0.6850 0.01940 0.01002 -0.0434 0.3636 1.0000
4.250 0.7070 0.01976 0.01037 -0.0423 0.3583 1.0000
4.500 0.7295 0.02008 0.01064 -0.0413 0.3536 1.0000
4.750 0.7524 0.02040 0.01086 -0.0403 0.3497 1.0000
5.000 0.7759 0.02072 0.01104 -0.0394 0.3464 1.0000
5.250 0.7987 0.02113 0.01142 -0.0384 0.3428 1.0000
5.500 0.8209 0.02157 0.01188 -0.0375 0.3388 1.0000
5.750 0.8436 0.02199 0.01228 -0.0365 0.3352 1.0000
6.000 0.8667 0.02240 0.01263 -0.0357 0.3320 1.0000
6.250 0.8904 0.02279 0.01295 -0.0349 0.3292 1.0000
6.500 0.9149 0.02321 0.01325 -0.0342 0.3267 1.0000
6.750 0.9353 0.02379 0.01393 -0.0331 0.3232 1.0000
7.000 0.9563 0.02434 0.01453 -0.0321 0.3198 1.0000
7.250 0.9780 0.02487 0.01507 -0.0311 0.3168 1.0000
7.500 1.0004 0.02537 0.01557 -0.0302 0.3142 1.0000
7.750 1.0236 0.02587 0.01603 -0.0295 0.3120 1.0000
8.000 1.0475 0.02637 0.01649 -0.0288 0.3100 1.0000
8.250 1.0701 0.02700 0.01710 -0.0281 0.3080 1.0000
8.500 1.0870 0.02782 0.01806 -0.0267 0.3056 1.0000
8.750 1.1041 0.02864 0.01900 -0.0255 0.3032 1.0000
9.000 1.1215 0.02946 0.01991 -0.0242 0.3008 1.0000
9.250 1.1395 0.03020 0.02071 -0.0231 0.2984 1.0000
9.500 1.1592 0.03079 0.02131 -0.0220 0.2958 1.0000
9.750 1.1823 0.03121 0.02168 -0.0213 0.2933 1.0000
10.000 1.2087 0.03161 0.02199 -0.0210 0.2909 1.0000
10.250 1.2112 0.03288 0.02350 -0.0183 0.2879 1.0000
10.500 1.2150 0.03406 0.02485 -0.0159 0.2847 1.0000
10.750 1.2213 0.03505 0.02593 -0.0137 0.2817 1.0000
11.000 1.2331 0.03572 0.02663 -0.0118 0.2788 1.0000
11.250 1.2553 0.03600 0.02685 -0.0110 0.2760 1.0000
11.500 1.2790 0.03634 0.02712 -0.0103 0.2733 1.0000
11.750 1.2525 0.03873 0.02978 -0.0060 0.2704 1.0000
12.000 1.2264 0.04181 0.03308 -0.0035 0.2671 1.0000
12.250 1.2065 0.04513 0.03656 -0.0024 0.2640 1.0000
12.500 1.2095 0.04696 0.03843 -0.0017 0.2613 1.0000
12.750 1.2383 0.04670 0.03813 -0.0010 0.2591 1.0000
13.000 1.2739 0.04600 0.03735 -0.0003 0.2570 1.0000
13.250 1.0133 0.07827 0.07030 -0.0110 0.2416 1.0000
13.500 1.0494 0.07617 0.06819 -0.0093 0.2410 1.0000
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Polar data table (+)
Polar graphs
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