EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 856 AIRFOIL (e856-il) Reynolds number: 500,000 Max Cl/Cd: 100.79 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e856-il-500000.txt Download as CSV file: xf-e856-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 856 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6051 0.09914 0.09610 -0.0622 1.0000 0.0104
-15.500 -0.6342 0.08962 0.08636 -0.0676 1.0000 0.0103
-15.250 -0.6430 0.08440 0.08103 -0.0705 1.0000 0.0102
-15.000 -0.6575 0.07879 0.07532 -0.0730 1.0000 0.0101
-14.750 -0.6843 0.07148 0.06780 -0.0768 1.0000 0.0102
-14.500 -0.6898 0.06780 0.06405 -0.0784 1.0000 0.0101
-14.250 -0.7025 0.06352 0.05966 -0.0797 1.0000 0.0101
-14.000 -0.7166 0.05929 0.05530 -0.0813 1.0000 0.0101
-13.750 -0.7281 0.05569 0.05158 -0.0820 1.0000 0.0101
-13.500 -0.7436 0.05188 0.04766 -0.0823 1.0000 0.0102
-13.250 -0.7473 0.04958 0.04528 -0.0822 1.0000 0.0101
-13.000 -0.7645 0.04613 0.04172 -0.0814 1.0000 0.0103
-12.750 -0.7753 0.04364 0.03916 -0.0803 1.0000 0.0103
-12.500 -0.7694 0.04076 0.03620 -0.0826 0.9982 0.0105
-12.250 -0.7493 0.03811 0.03349 -0.0871 0.9950 0.0108
-12.000 -0.7299 0.03553 0.03079 -0.0911 0.9913 0.0109
-11.750 -0.7083 0.03323 0.02839 -0.0950 0.9869 0.0110
-11.500 -0.6825 0.03105 0.02611 -0.0995 0.9839 0.0114
-11.250 -0.6647 0.02898 0.02393 -0.1020 0.9770 0.0116
-11.000 -0.6390 0.02710 0.02193 -0.1059 0.9728 0.0120
-10.750 -0.6265 0.02537 0.02011 -0.1065 0.9627 0.0122
-10.500 -0.6086 0.02399 0.01860 -0.1068 0.9530 0.0125
-10.250 -0.5898 0.02239 0.01692 -0.1072 0.9436 0.0128
-10.000 -0.5666 0.02086 0.01536 -0.1084 0.9361 0.0135
-9.750 -0.5456 0.01979 0.01424 -0.1083 0.9251 0.0140
-9.500 -0.5146 0.01875 0.01313 -0.1100 0.9175 0.0148
-9.250 -0.4809 0.01758 0.01186 -0.1124 0.9085 0.0160
-9.000 -0.4398 0.01663 0.01087 -0.1160 0.8991 0.0179
-8.750 -0.3890 0.01554 0.00970 -0.1219 0.8898 0.0202
-8.500 -0.3376 0.01464 0.00871 -0.1278 0.8748 0.0241
-8.250 -0.2963 0.01396 0.00792 -0.1313 0.8548 0.0293
-8.000 -0.2665 0.01349 0.00735 -0.1323 0.8324 0.0353
-7.750 -0.2413 0.01312 0.00687 -0.1322 0.8117 0.0422
-7.500 -0.2184 0.01279 0.00646 -0.1316 0.7929 0.0495
-7.250 -0.1962 0.01249 0.00609 -0.1308 0.7757 0.0578
-7.000 -0.1743 0.01218 0.00573 -0.1299 0.7595 0.0682
-6.750 -0.1524 0.01187 0.00540 -0.1290 0.7442 0.0811
-6.500 -0.1302 0.01156 0.00508 -0.1282 0.7299 0.0976
-6.000 -0.0851 0.01092 0.00447 -0.1267 0.7042 0.1465
-5.750 -0.0629 0.01046 0.00414 -0.1260 0.6924 0.1874
-5.500 -0.0411 0.00995 0.00381 -0.1253 0.6814 0.2497
-5.250 -0.0181 0.00960 0.00362 -0.1247 0.6704 0.3126
-5.000 0.0070 0.00947 0.00353 -0.1242 0.6599 0.3490
-4.750 0.0329 0.00947 0.00347 -0.1238 0.6500 0.3726
-4.500 0.0592 0.00948 0.00343 -0.1235 0.6402 0.3896
-4.250 0.0856 0.00951 0.00341 -0.1231 0.6315 0.4033
-4.000 0.1121 0.00955 0.00339 -0.1228 0.6226 0.4155
-3.750 0.1389 0.00963 0.00337 -0.1225 0.6145 0.4266
-3.500 0.1654 0.00968 0.00337 -0.1222 0.6061 0.4358
-3.250 0.1922 0.00975 0.00334 -0.1220 0.5985 0.4434
-3.000 0.2189 0.00977 0.00334 -0.1217 0.5908 0.4505
-2.750 0.2458 0.00989 0.00332 -0.1215 0.5841 0.4575
-2.500 0.2727 0.00987 0.00332 -0.1212 0.5774 0.4642
-2.250 0.2995 0.00996 0.00334 -0.1210 0.5709 0.4719
-2.000 0.3263 0.01004 0.00337 -0.1208 0.5648 0.4801
-1.750 0.3532 0.01008 0.00340 -0.1205 0.5585 0.4870
-1.500 0.3801 0.01017 0.00339 -0.1203 0.5528 0.4923
-1.250 0.4072 0.01019 0.00338 -0.1202 0.5476 0.4968
-1.000 0.4342 0.01020 0.00340 -0.1200 0.5424 0.5013
-0.750 0.4611 0.01026 0.00341 -0.1199 0.5373 0.5060
-0.500 0.4884 0.01038 0.00343 -0.1198 0.5324 0.5104
-0.250 0.5152 0.01036 0.00344 -0.1196 0.5277 0.5148
0.000 0.5419 0.01039 0.00347 -0.1194 0.5230 0.5195
0.250 0.5689 0.01049 0.00351 -0.1193 0.5188 0.5242
0.500 0.5964 0.01059 0.00356 -0.1193 0.5148 0.5287
0.750 0.6230 0.01059 0.00360 -0.1191 0.5108 0.5335
1.000 0.6496 0.01064 0.00366 -0.1189 0.5067 0.5386
1.250 0.6765 0.01074 0.00371 -0.1187 0.5027 0.5437
1.500 0.7040 0.01087 0.00380 -0.1188 0.4989 0.5487
1.750 0.7302 0.01088 0.00388 -0.1185 0.4955 0.5541
2.000 0.7567 0.01095 0.00396 -0.1183 0.4920 0.5601
2.250 0.7834 0.01104 0.00403 -0.1181 0.4886 0.5658
2.500 0.8102 0.01114 0.00414 -0.1180 0.4851 0.5716
2.750 0.8374 0.01127 0.00427 -0.1180 0.4817 0.5784
3.000 0.8630 0.01132 0.00437 -0.1177 0.4785 0.5853
3.250 0.8889 0.01138 0.00449 -0.1174 0.4753 0.5927
3.500 0.9151 0.01148 0.00459 -0.1171 0.4722 0.6006
3.750 0.9417 0.01160 0.00473 -0.1170 0.4692 0.6086
4.000 0.9696 0.01179 0.00491 -0.1172 0.4659 0.6182
4.250 0.9940 0.01183 0.00505 -0.1166 0.4631 0.6282
4.500 1.0189 0.01190 0.00520 -0.1162 0.4600 0.6392
4.750 1.0443 0.01200 0.00534 -0.1158 0.4571 0.6516
5.000 1.0697 0.01210 0.00550 -0.1155 0.4543 0.6652
5.250 1.0968 0.01228 0.00571 -0.1155 0.4512 0.6811
5.500 1.1220 0.01240 0.00593 -0.1152 0.4484 0.6998
6.000 1.1681 0.01251 0.00630 -0.1135 0.4428 0.7477
6.250 1.1903 0.01256 0.00648 -0.1125 0.4399 0.7819
6.500 1.2109 0.01258 0.00667 -0.1111 0.4371 0.8350
6.750 1.2442 0.01267 0.00693 -0.1123 0.4335 1.0000
7.000 1.2640 0.01277 0.00710 -0.1109 0.4310 1.0000
7.250 1.2842 0.01289 0.00728 -0.1096 0.4275 1.0000
7.500 1.3049 0.01304 0.00744 -0.1084 0.4239 1.0000
7.750 1.3264 0.01322 0.00760 -0.1074 0.4200 1.0000
8.000 1.3483 0.01345 0.00784 -0.1065 0.4158 1.0000
8.250 1.3651 0.01357 0.00803 -0.1045 0.4116 1.0000
8.500 1.3829 0.01372 0.00821 -0.1028 0.4071 1.0000
8.750 1.4029 0.01396 0.00842 -0.1016 0.4025 1.0000
9.000 1.4213 0.01417 0.00869 -0.1000 0.3984 1.0000
9.250 1.4388 0.01435 0.00894 -0.0984 0.3939 1.0000
9.500 1.4565 0.01457 0.00919 -0.0968 0.3895 1.0000
9.750 1.4756 0.01489 0.00949 -0.0955 0.3850 1.0000
10.000 1.4922 0.01511 0.00982 -0.0938 0.3807 1.0000
10.250 1.5080 0.01537 0.01014 -0.0919 0.3754 1.0000
10.500 1.5234 0.01573 0.01049 -0.0901 0.3702 1.0000
10.750 1.5390 0.01604 0.01090 -0.0883 0.3646 1.0000
11.000 1.5534 0.01641 0.01131 -0.0864 0.3585 1.0000
11.250 1.5657 0.01688 0.01180 -0.0843 0.3521 1.0000
11.500 1.5788 0.01733 0.01232 -0.0823 0.3442 1.0000
11.750 1.5889 0.01793 0.01294 -0.0800 0.3368 1.0000
12.000 1.5998 0.01855 0.01361 -0.0780 0.3276 1.0000
12.250 1.6085 0.01931 0.01440 -0.0757 0.3185 1.0000
12.500 1.6126 0.02032 0.01540 -0.0730 0.3077 1.0000
12.750 1.6176 0.02138 0.01649 -0.0706 0.2948 1.0000
13.000 1.6179 0.02278 0.01787 -0.0679 0.2801 1.0000
13.250 1.6136 0.02457 0.01963 -0.0649 0.2640 1.0000
13.500 1.6064 0.02671 0.02174 -0.0621 0.2471 1.0000
13.750 1.5963 0.02926 0.02424 -0.0595 0.2293 1.0000
14.000 1.5837 0.03220 0.02714 -0.0571 0.2127 1.0000
14.250 1.5703 0.03542 0.03033 -0.0550 0.1979 1.0000
14.500 1.5565 0.03890 0.03379 -0.0533 0.1845 1.0000
14.750 1.5423 0.04259 0.03747 -0.0520 0.1723 1.0000
15.250 1.5155 0.05035 0.04523 -0.0502 0.1497 1.0000
15.500 1.5037 0.05429 0.04918 -0.0497 0.1401 1.0000
15.750 1.4907 0.05850 0.05340 -0.0494 0.1318 1.0000
16.000 1.4804 0.06252 0.05744 -0.0493 0.1228 1.0000
16.250 1.4715 0.06648 0.06143 -0.0494 0.1156 1.0000
16.500 1.4611 0.07072 0.06567 -0.0496 0.1085 1.0000
16.750 1.4551 0.07451 0.06950 -0.0499 0.1020 1.0000
17.000 1.4459 0.07876 0.07376 -0.0504 0.0958 1.0000
17.250 1.4416 0.08246 0.07751 -0.0509 0.0901 1.0000
17.500 1.4339 0.08668 0.08175 -0.0516 0.0846 1.0000
17.750 1.4305 0.09038 0.08548 -0.0523 0.0792 1.0000
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Polar data table (+)
Polar graphs
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