EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 393 AIRFOIL (e393-il) Reynolds number: 100,000 Max Cl/Cd: 60.63 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e393-il-100000.txt Download as CSV file: xf-e393-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3104 0.10674 0.10201 -0.0425 1.0000 0.0909
-9.000 -0.3276 0.10530 0.10071 -0.0447 1.0000 0.0930
-8.750 -0.3509 0.10420 0.09978 -0.0461 1.0000 0.0936
-8.500 -0.3244 0.09863 0.09418 -0.0422 1.0000 0.0965
-8.250 -0.3200 0.09649 0.09209 -0.0400 1.0000 0.1015
-8.000 -0.3312 0.09476 0.09048 -0.0387 1.0000 0.1038
-7.750 -0.3489 0.09356 0.08942 -0.0365 1.0000 0.1049
-7.500 -0.3805 0.09354 0.08957 -0.0329 1.0000 0.1061
-7.250 -0.4071 0.09333 0.08950 -0.0287 1.0000 0.1062
-7.000 -0.4342 0.09284 0.08914 -0.0264 1.0000 0.1065
-6.750 -0.4121 0.08799 0.08430 -0.0293 0.9948 0.1118
-6.500 -0.3898 0.07878 0.07499 -0.0542 0.9795 0.1226
-6.250 -0.3639 0.07795 0.07421 -0.0452 0.9765 0.1290
-6.000 -0.3407 0.07138 0.06759 -0.0572 0.9660 0.1398
-5.750 -0.3130 0.06547 0.06156 -0.0675 0.9574 0.1531
-5.500 -0.2908 0.06085 0.05680 -0.0736 0.9472 0.1670
-5.250 -0.2402 0.04017 0.03438 -0.0943 0.9406 0.0707
-5.000 -0.2029 0.03499 0.02836 -0.0978 0.9336 0.0628
-4.750 -0.1578 0.03095 0.02358 -0.1018 0.9298 0.0614
-4.500 -0.1252 0.02911 0.02112 -0.1029 0.9213 0.0657
-4.250 -0.0830 0.02645 0.01821 -0.1059 0.9172 0.0716
-4.000 -0.0490 0.02524 0.01666 -0.1068 0.9096 0.0801
-3.750 -0.0095 0.02344 0.01487 -0.1089 0.9045 0.0947
-3.500 0.0354 0.02180 0.01341 -0.1122 0.9014 0.1250
-3.250 0.0624 0.02060 0.01258 -0.1125 0.8924 0.1854
-3.000 0.1044 0.01877 0.01211 -0.1158 0.8888 0.4623
-2.750 0.1299 0.01889 0.01238 -0.1148 0.8802 0.5641
-2.500 0.1650 0.01884 0.01230 -0.1152 0.8750 0.6284
-2.250 0.1886 0.01898 0.01241 -0.1138 0.8667 0.6714
-2.000 0.2191 0.01888 0.01230 -0.1132 0.8611 0.7109
-1.750 0.2408 0.01898 0.01237 -0.1114 0.8530 0.7445
-1.500 0.2676 0.01885 0.01222 -0.1102 0.8471 0.7769
-1.250 0.2859 0.01894 0.01228 -0.1078 0.8390 0.8072
-1.000 0.3094 0.01879 0.01210 -0.1060 0.8329 0.8395
-0.750 0.3246 0.01885 0.01215 -0.1031 0.8248 0.8733
-0.500 0.3467 0.01862 0.01189 -0.1011 0.8188 0.9134
-0.250 0.3935 0.01833 0.01152 -0.1044 0.8139 0.9640
0.000 0.4389 0.01837 0.01142 -0.1093 0.8065 1.0000
0.250 0.4814 0.01826 0.01113 -0.1127 0.8022 1.0000
0.500 0.5067 0.01878 0.01152 -0.1137 0.7928 1.0000
0.750 0.5455 0.01875 0.01134 -0.1158 0.7883 1.0000
1.000 0.5685 0.01934 0.01186 -0.1159 0.7793 1.0000
1.250 0.6043 0.01936 0.01177 -0.1173 0.7745 1.0000
1.500 0.6263 0.01998 0.01234 -0.1170 0.7657 1.0000
1.750 0.6602 0.02005 0.01235 -0.1180 0.7607 1.0000
2.000 0.6821 0.02069 0.01297 -0.1175 0.7522 1.0000
2.250 0.7146 0.02080 0.01304 -0.1183 0.7469 1.0000
2.500 0.7366 0.02144 0.01368 -0.1178 0.7386 1.0000
2.750 0.7680 0.02159 0.01382 -0.1183 0.7329 1.0000
3.000 0.7901 0.02222 0.01448 -0.1178 0.7247 1.0000
3.250 0.8212 0.02236 0.01461 -0.1181 0.7187 1.0000
3.500 0.8430 0.02300 0.01529 -0.1175 0.7103 1.0000
3.750 0.8749 0.02304 0.01537 -0.1179 0.7042 1.0000
4.000 0.8960 0.02367 0.01607 -0.1170 0.6950 1.0000
4.250 0.9304 0.02352 0.01593 -0.1175 0.6890 1.0000
4.500 0.9501 0.02418 0.01668 -0.1165 0.6790 1.0000
4.750 0.9876 0.02380 0.01635 -0.1172 0.6734 1.0000
5.000 1.0071 0.02439 0.01705 -0.1161 0.6625 1.0000
5.250 1.0316 0.02466 0.01741 -0.1153 0.6525 1.0000
5.500 1.0688 0.02412 0.01690 -0.1158 0.6451 1.0000
5.750 1.0908 0.02441 0.01734 -0.1146 0.6333 1.0000
6.000 1.1159 0.02446 0.01751 -0.1138 0.6217 1.0000
6.250 1.1438 0.02427 0.01741 -0.1131 0.6100 1.0000
6.500 1.1729 0.02395 0.01719 -0.1124 0.5977 1.0000
6.750 1.2010 0.02363 0.01695 -0.1117 0.5844 1.0000
7.000 1.2268 0.02333 0.01681 -0.1105 0.5692 1.0000
7.250 1.2516 0.02301 0.01660 -0.1092 0.5524 1.0000
7.500 1.2773 0.02257 0.01626 -0.1080 0.5341 1.0000
7.750 1.2992 0.02230 0.01609 -0.1062 0.5132 1.0000
8.000 1.3202 0.02199 0.01584 -0.1042 0.4885 1.0000
8.250 1.3343 0.02201 0.01602 -0.1014 0.4577 1.0000
8.500 1.3460 0.02220 0.01622 -0.0983 0.4193 1.0000
8.750 1.3516 0.02280 0.01671 -0.0945 0.3708 1.0000
9.000 1.3506 0.02395 0.01754 -0.0899 0.3167 1.0000
9.250 1.3432 0.02554 0.01878 -0.0849 0.2695 1.0000
9.500 1.3344 0.02745 0.02040 -0.0801 0.2301 1.0000
9.750 1.3260 0.02960 0.02228 -0.0759 0.1971 1.0000
10.000 1.3184 0.03193 0.02439 -0.0724 0.1690 1.0000
10.250 1.3122 0.03439 0.02669 -0.0694 0.1435 1.0000
10.500 1.3065 0.03700 0.02917 -0.0669 0.1210 1.0000
10.750 1.3004 0.03981 0.03182 -0.0648 0.1020 1.0000
11.000 1.2960 0.04274 0.03470 -0.0630 0.0837 1.0000
11.250 1.2923 0.04580 0.03771 -0.0613 0.0689 1.0000
11.500 1.2916 0.04885 0.04072 -0.0597 0.0575 1.0000
11.750 1.2952 0.05171 0.04359 -0.0583 0.0493 1.0000
12.000 1.3026 0.05421 0.04612 -0.0571 0.0437 1.0000
12.250 1.3263 0.05675 0.04872 -0.0555 0.0395 1.0000
12.500 1.3446 0.05949 0.05173 -0.0542 0.0370 1.0000
12.750 1.3586 0.06263 0.05513 -0.0532 0.0355 1.0000
13.000 1.3659 0.06604 0.05878 -0.0523 0.0344 1.0000
13.250 1.3703 0.06963 0.06255 -0.0517 0.0333 1.0000
13.500 1.3739 0.07439 0.06749 -0.0512 0.0322 1.0000
13.750 1.3648 0.08007 0.07346 -0.0509 0.0317 1.0000
14.000 1.3497 0.08463 0.07833 -0.0510 0.0316 1.0000
14.250 1.3338 0.08967 0.08366 -0.0516 0.0315 1.0000
14.500 1.3167 0.09512 0.08939 -0.0528 0.0315 1.0000
14.750 1.2992 0.10101 0.09554 -0.0544 0.0316 1.0000
15.000 1.2815 0.10730 0.10206 -0.0567 0.0317 1.0000
15.250 1.2637 0.11359 0.10861 -0.0596 0.0318 1.0000
15.500 1.2449 0.12002 0.11527 -0.0633 0.0320 1.0000
15.750 0.9789 0.13589 0.13235 -0.0703 0.0402 1.0000
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Polar data table (+)
Polar graphs
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