EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Reynolds number: 500,000 Max Cl/Cd: 103.4 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ec863914-il-500000.txt Download as CSV file: xf-ec863914-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EC 86(-3)-914 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4182 0.06302 0.06046 -0.1132 0.9587 0.0236
-10.000 -0.4523 0.05803 0.05533 -0.1146 0.9543 0.0227
-9.750 -0.4865 0.05508 0.05227 -0.1119 0.9485 0.0222
-9.500 -0.4991 0.05235 0.04942 -0.1126 0.9455 0.0226
-9.250 -0.5231 0.05039 0.04737 -0.1095 0.9393 0.0225
-9.000 -0.5257 0.04779 0.04462 -0.1102 0.9345 0.0232
-8.750 -0.4915 0.05070 0.04728 -0.1130 0.9323 0.0272
-6.750 -0.3202 0.02328 0.01763 -0.1215 0.9178 0.0126
-6.500 -0.2825 0.02191 0.01612 -0.1241 0.9173 0.0115
-6.250 -0.2676 0.02122 0.01533 -0.1225 0.9117 0.0112
-6.000 -0.2327 0.02041 0.01444 -0.1247 0.9100 0.0112
-5.750 -0.1955 0.01972 0.01367 -0.1272 0.9088 0.0114
-5.500 -0.1582 0.01921 0.01308 -0.1296 0.9077 0.0116
-5.250 -0.1204 0.01874 0.01255 -0.1321 0.9068 0.0124
-5.000 -0.0824 0.01837 0.01209 -0.1343 0.9060 0.0128
-4.750 -0.0446 0.01809 0.01172 -0.1365 0.9053 0.0128
-4.500 -0.0065 0.01785 0.01141 -0.1386 0.9046 0.0130
-4.250 0.0317 0.01764 0.01116 -0.1408 0.9041 0.0133
-3.750 0.0948 0.01660 0.01070 -0.1441 0.8973 0.1528
-3.500 0.1300 0.01639 0.01056 -0.1458 0.8954 0.1760
-3.250 0.1675 0.01614 0.01042 -0.1479 0.8941 0.2061
-3.000 0.2067 0.01584 0.01024 -0.1504 0.8931 0.2366
-2.750 0.2474 0.01551 0.01000 -0.1531 0.8923 0.2613
-2.500 0.2922 0.01499 0.00975 -0.1570 0.8918 0.3210
-2.250 0.3391 0.01440 0.00945 -0.1615 0.8914 0.4028
-2.000 0.3896 0.01364 0.00919 -0.1667 0.8912 0.5335
-1.750 0.4176 0.01347 0.00923 -0.1666 0.8860 0.6068
-1.500 0.4529 0.01316 0.00893 -0.1676 0.8824 0.6340
-1.250 0.4926 0.01281 0.00855 -0.1696 0.8807 0.6502
-1.000 0.5324 0.01242 0.00817 -0.1715 0.8795 0.6606
-0.750 0.5768 0.01183 0.00756 -0.1743 0.8786 0.6694
-0.500 0.6214 0.01125 0.00698 -0.1772 0.8779 0.6773
-0.250 0.6647 0.01083 0.00657 -0.1799 0.8771 0.6838
0.000 0.6722 0.01097 0.00675 -0.1755 0.8679 0.6887
0.250 0.7124 0.01060 0.00635 -0.1778 0.8659 0.6949
0.500 0.7514 0.01024 0.00603 -0.1797 0.8641 0.6984
0.750 0.7621 0.01032 0.00614 -0.1759 0.8547 0.7020
1.000 0.8003 0.00996 0.00578 -0.1777 0.8506 0.7071
1.250 0.8162 0.00999 0.00583 -0.1751 0.8394 0.7110
1.500 0.8376 0.00995 0.00583 -0.1735 0.8284 0.7137
1.750 0.8643 0.00984 0.00574 -0.1729 0.8159 0.7179
2.000 0.8992 0.00965 0.00552 -0.1741 0.7994 0.7242
2.250 0.9370 0.00940 0.00521 -0.1757 0.7747 0.7275
2.500 0.9740 0.00942 0.00505 -0.1771 0.7365 0.7307
2.750 0.9954 0.00980 0.00520 -0.1756 0.6930 0.7349
3.000 1.0088 0.01030 0.00547 -0.1726 0.6492 0.7398
3.250 1.0155 0.01088 0.00588 -0.1681 0.6073 0.7435
3.500 1.0244 0.01150 0.00630 -0.1643 0.5653 0.7478
3.750 1.0380 0.01210 0.00670 -0.1618 0.5232 0.7515
4.000 1.0542 0.01268 0.00707 -0.1598 0.4830 0.7534
4.250 1.0691 0.01323 0.00745 -0.1576 0.4467 0.7546
4.500 1.0862 0.01375 0.00782 -0.1558 0.4117 0.7558
4.750 1.1043 0.01429 0.00821 -0.1542 0.3792 0.7569
5.000 1.1231 0.01481 0.00861 -0.1528 0.3505 0.7582
5.250 1.1427 0.01532 0.00900 -0.1516 0.3266 0.7597
5.500 1.1635 0.01579 0.00939 -0.1506 0.3056 0.7611
5.750 1.1844 0.01628 0.00980 -0.1497 0.2877 0.7624
6.000 1.2060 0.01675 0.01020 -0.1489 0.2724 0.7637
6.250 1.2283 0.01720 0.01063 -0.1482 0.2592 0.7650
6.500 1.2505 0.01765 0.01104 -0.1475 0.2466 0.7664
6.750 1.2720 0.01812 0.01147 -0.1468 0.2330 0.7678
7.000 1.2929 0.01856 0.01189 -0.1458 0.2213 0.7689
7.250 1.3137 0.01902 0.01234 -0.1449 0.2119 0.7699
7.500 1.3341 0.01950 0.01281 -0.1439 0.2022 0.7710
7.750 1.3559 0.01991 0.01324 -0.1432 0.1924 0.7722
8.000 1.3761 0.02043 0.01374 -0.1422 0.1775 0.7734
8.250 1.3945 0.02111 0.01428 -0.1411 0.1531 0.7747
8.500 1.4011 0.02284 0.01544 -0.1383 0.0792 0.7759
8.750 1.3972 0.02565 0.01774 -0.1340 0.0114 0.7772
9.000 1.4121 0.02675 0.01891 -0.1323 0.0083 0.7788
9.250 1.4286 0.02769 0.01994 -0.1309 0.0074 0.7803
9.500 1.4438 0.02876 0.02111 -0.1293 0.0067 0.7815
9.750 1.4559 0.03003 0.02249 -0.1274 0.0062 0.7826
10.000 1.4643 0.03161 0.02422 -0.1249 0.0058 0.7837
10.250 1.4678 0.03358 0.02638 -0.1220 0.0056 0.7848
10.500 1.4764 0.03512 0.02804 -0.1198 0.0055 0.7860
10.750 1.4829 0.03684 0.02988 -0.1175 0.0054 0.7872
11.000 1.4874 0.03877 0.03194 -0.1152 0.0053 0.7885
11.250 1.4911 0.04084 0.03414 -0.1129 0.0052 0.7898
11.500 1.4951 0.04294 0.03636 -0.1108 0.0051 0.7913
11.750 1.4980 0.04521 0.03875 -0.1089 0.0050 0.7929
12.000 1.5004 0.04765 0.04130 -0.1071 0.0048 0.7944
12.250 1.5027 0.05018 0.04395 -0.1056 0.0046 0.7959
12.500 1.5050 0.05274 0.04661 -0.1042 0.0044 0.7971
12.750 1.5028 0.05592 0.04994 -0.1028 0.0044 0.7982
13.000 1.5019 0.05910 0.05324 -0.1017 0.0042 0.7995
13.250 1.4990 0.06268 0.05695 -0.1009 0.0042 0.8007
13.500 1.4958 0.06645 0.06088 -0.1003 0.0041 0.8020
13.750 1.4917 0.07050 0.06506 -0.1000 0.0040 0.8033
14.000 1.4876 0.07473 0.06941 -0.1001 0.0040 0.8047
14.250 1.4829 0.07922 0.07405 -0.1004 0.0040 0.8060
14.500 1.4785 0.08378 0.07875 -0.1010 0.0039 0.8073
14.750 1.4733 0.08855 0.08363 -0.1019 0.0039 0.8086
15.000 1.4685 0.09343 0.08864 -0.1029 0.0038 0.8098
15.250 1.4639 0.09832 0.09367 -0.1041 0.0038 0.8109
15.500 1.4596 0.10323 0.09872 -0.1056 0.0038 0.8121
15.750 1.4547 0.10826 0.10389 -0.1071 0.0038 0.8132
16.000 1.4483 0.11344 0.10921 -0.1085 0.0036 0.8142
16.250 1.4417 0.11883 0.11476 -0.1103 0.0036 0.8153
16.500 1.4386 0.12397 0.12004 -0.1130 0.0037 0.8171
16.750 1.4286 0.13013 0.12639 -0.1154 0.0036 0.8182
17.000 1.4240 0.13568 0.13209 -0.1187 0.0036 0.8200
17.250 1.4143 0.14221 0.13880 -0.1223 0.0036 0.8215
17.500 1.4113 0.14769 0.14440 -0.1261 0.0036 0.8235
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