EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 393 AIRFOIL (e393-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.45 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e393-il-1000000-n5.txt Download as CSV file: xf-e393-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 393 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3571 0.11540 0.11373 -0.0381 1.0000 0.0040
-11.250 -0.3520 0.11090 0.10923 -0.0407 0.9995 0.0038
-10.750 -0.5709 0.04168 0.03986 -0.0890 0.9849 0.0040
-10.250 -0.5625 0.02541 0.02265 -0.1133 0.9597 0.0040
-10.000 -0.5403 0.02272 0.01964 -0.1160 0.9482 0.0040
-9.750 -0.5154 0.02049 0.01709 -0.1181 0.9324 0.0041
-9.500 -0.4917 0.01878 0.01507 -0.1190 0.9109 0.0042
-9.250 -0.4692 0.01769 0.01372 -0.1191 0.8877 0.0042
-9.000 -0.4465 0.01691 0.01272 -0.1188 0.8665 0.0043
-8.750 -0.4236 0.01615 0.01176 -0.1185 0.8472 0.0044
-8.500 -0.3998 0.01553 0.01095 -0.1182 0.8295 0.0045
-8.250 -0.3755 0.01492 0.01017 -0.1180 0.8134 0.0045
-8.000 -0.3528 0.01368 0.00866 -0.1179 0.7988 0.0047
-7.750 -0.3284 0.01280 0.00757 -0.1177 0.7852 0.0049
-7.500 -0.3029 0.01219 0.00680 -0.1177 0.7723 0.0052
-7.250 -0.2765 0.01175 0.00626 -0.1176 0.7605 0.0054
-7.000 -0.2498 0.01139 0.00580 -0.1177 0.7496 0.0057
-6.750 -0.2229 0.01104 0.00534 -0.1177 0.7394 0.0060
-6.500 -0.1959 0.01072 0.00492 -0.1177 0.7295 0.0063
-6.250 -0.1685 0.01041 0.00452 -0.1177 0.7202 0.0066
-6.000 -0.1409 0.01015 0.00416 -0.1178 0.7117 0.0069
-5.750 -0.1134 0.00990 0.00383 -0.1179 0.7031 0.0071
-5.500 -0.0855 0.00961 0.00346 -0.1180 0.6954 0.0076
-5.000 -0.0296 0.00917 0.00291 -0.1182 0.6808 0.0097
-4.500 0.0267 0.00882 0.00250 -0.1185 0.6674 0.0144
-4.250 0.0548 0.00869 0.00231 -0.1186 0.6609 0.0170
-4.000 0.0832 0.00854 0.00215 -0.1188 0.6552 0.0202
-3.750 0.1116 0.00842 0.00199 -0.1189 0.6491 0.0231
-3.500 0.1398 0.00830 0.00185 -0.1191 0.6435 0.0292
-3.250 0.1684 0.00813 0.00172 -0.1193 0.6381 0.0429
-3.000 0.1967 0.00796 0.00160 -0.1196 0.6327 0.0640
-2.750 0.2252 0.00780 0.00149 -0.1198 0.6277 0.0880
-2.500 0.2538 0.00767 0.00140 -0.1200 0.6222 0.1108
-2.250 0.2822 0.00755 0.00132 -0.1202 0.6173 0.1383
-1.750 0.3395 0.00716 0.00119 -0.1209 0.6075 0.2398
-1.500 0.3680 0.00692 0.00114 -0.1213 0.6025 0.3160
-1.250 0.3967 0.00678 0.00112 -0.1216 0.5981 0.3640
-1.000 0.4253 0.00670 0.00111 -0.1218 0.5931 0.4008
-0.500 0.4823 0.00660 0.00113 -0.1222 0.5836 0.4694
-0.250 0.5108 0.00659 0.00115 -0.1224 0.5785 0.4906
0.250 0.5676 0.00659 0.00120 -0.1227 0.5689 0.5294
0.500 0.5960 0.00660 0.00123 -0.1228 0.5637 0.5455
0.750 0.6241 0.00663 0.00127 -0.1229 0.5587 0.5619
1.000 0.6526 0.00664 0.00131 -0.1231 0.5536 0.5790
1.250 0.6807 0.00667 0.00136 -0.1231 0.5479 0.5954
1.500 0.7089 0.00670 0.00142 -0.1232 0.5421 0.6121
2.000 0.7647 0.00679 0.00154 -0.1234 0.5264 0.6428
2.250 0.7925 0.00685 0.00162 -0.1234 0.5185 0.6579
2.500 0.8203 0.00689 0.00170 -0.1235 0.5107 0.6736
2.750 0.8477 0.00697 0.00179 -0.1234 0.5011 0.6909
3.000 0.8753 0.00704 0.00188 -0.1234 0.4914 0.7098
3.250 0.9027 0.00710 0.00200 -0.1234 0.4826 0.7303
3.500 0.9297 0.00719 0.00211 -0.1233 0.4710 0.7529
3.750 0.9562 0.00729 0.00224 -0.1231 0.4572 0.7779
4.000 0.9825 0.00740 0.00238 -0.1229 0.4444 0.8059
4.250 1.0081 0.00750 0.00255 -0.1225 0.4301 0.8384
4.500 1.0321 0.00762 0.00271 -0.1217 0.4127 0.8773
4.750 1.0514 0.00778 0.00288 -0.1199 0.3884 0.9333
5.000 1.0764 0.00803 0.00306 -0.1195 0.3621 1.0000
5.250 1.1003 0.00845 0.00333 -0.1190 0.3289 1.0000
5.500 1.1234 0.00893 0.00366 -0.1184 0.2937 1.0000
5.750 1.1443 0.00959 0.00408 -0.1174 0.2477 1.0000
6.000 1.1635 0.01038 0.00457 -0.1162 0.1948 1.0000
6.250 1.1828 0.01112 0.00506 -0.1150 0.1498 1.0000
6.500 1.2046 0.01164 0.00546 -0.1141 0.1253 1.0000
6.750 1.2267 0.01211 0.00585 -0.1134 0.1063 1.0000
7.000 1.2468 0.01271 0.00632 -0.1123 0.0820 1.0000
7.250 1.2665 0.01331 0.00680 -0.1111 0.0616 1.0000
7.500 1.2856 0.01393 0.00731 -0.1098 0.0437 1.0000
7.750 1.3044 0.01453 0.00783 -0.1085 0.0301 1.0000
8.000 1.3232 0.01510 0.00837 -0.1072 0.0205 1.0000
8.250 1.3413 0.01569 0.00892 -0.1058 0.0134 1.0000
8.500 1.3573 0.01636 0.00955 -0.1040 0.0070 1.0000
8.750 1.3728 0.01691 0.01011 -0.1020 0.0048 1.0000
9.000 1.3879 0.01743 0.01066 -0.1000 0.0040 1.0000
9.250 1.4021 0.01799 0.01126 -0.0979 0.0036 1.0000
9.500 1.4154 0.01861 0.01193 -0.0958 0.0031 1.0000
9.750 1.4286 0.01926 0.01263 -0.0936 0.0030 1.0000
10.000 1.4418 0.01992 0.01336 -0.0916 0.0029 1.0000
10.250 1.4543 0.02065 0.01414 -0.0896 0.0028 1.0000
10.500 1.4659 0.02145 0.01501 -0.0876 0.0026 1.0000
10.750 1.4767 0.02234 0.01596 -0.0856 0.0025 1.0000
11.000 1.4868 0.02332 0.01701 -0.0836 0.0025 1.0000
11.250 1.4961 0.02440 0.01815 -0.0817 0.0024 1.0000
11.500 1.5048 0.02557 0.01940 -0.0799 0.0023 1.0000
11.750 1.5134 0.02681 0.02070 -0.0782 0.0022 1.0000
12.000 1.5212 0.02818 0.02214 -0.0766 0.0021 1.0000
12.250 1.5285 0.02963 0.02369 -0.0751 0.0020 1.0000
12.500 1.5345 0.03128 0.02541 -0.0737 0.0020 1.0000
12.750 1.5401 0.03304 0.02725 -0.0724 0.0019 1.0000
13.000 1.5443 0.03499 0.02929 -0.0711 0.0019 1.0000
13.250 1.5476 0.03712 0.03151 -0.0700 0.0018 1.0000
13.500 1.5498 0.03943 0.03392 -0.0690 0.0018 1.0000
13.750 1.5503 0.04201 0.03660 -0.0682 0.0017 1.0000
14.000 1.5503 0.04475 0.03945 -0.0675 0.0017 1.0000
14.250 1.5473 0.04791 0.04274 -0.0669 0.0016 1.0000
14.500 1.5462 0.05098 0.04591 -0.0666 0.0016 1.0000
14.750 1.5395 0.05486 0.04994 -0.0665 0.0016 1.0000
15.000 1.5340 0.05875 0.05395 -0.0666 0.0016 1.0000
15.250 1.5324 0.06225 0.05756 -0.0668 0.0016 1.0000
15.500 1.5321 0.06568 0.06109 -0.0673 0.0015 1.0000
15.750 1.5281 0.06976 0.06530 -0.0680 0.0015 1.0000
16.000 1.5262 0.07362 0.06926 -0.0688 0.0015 1.0000
16.250 1.5200 0.07829 0.07406 -0.0699 0.0015 1.0000
16.500 1.5165 0.08267 0.07856 -0.0711 0.0015 1.0000
16.750 1.5104 0.08756 0.08357 -0.0726 0.0015 1.0000
17.000 1.5048 0.09252 0.08864 -0.0743 0.0015 1.0000
17.250 1.4973 0.09796 0.09421 -0.0764 0.0015 1.0000
17.500 1.4886 0.10372 0.10010 -0.0787 0.0015 1.0000
17.750 1.4807 0.10946 0.10595 -0.0811 0.0015 1.0000
18.000 1.4706 0.11575 0.11238 -0.0840 0.0015 1.0000
18.250 1.4611 0.12205 0.11880 -0.0870 0.0015 1.0000
18.500 1.4510 0.12860 0.12549 -0.0904 0.0015 1.0000
18.750 1.4402 0.13540 0.13241 -0.0940 0.0015 1.0000
19.000 1.4301 0.14218 0.13931 -0.0978 0.0014 1.0000
19.250 1.4194 0.14919 0.14644 -0.1019 0.0014 1.0000
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