EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 748 AIRFOIL (e748-il) Reynolds number: 100,000 Max Cl/Cd: 31.42 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e748-il-100000.txt Download as CSV file: xf-e748-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 748 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5865 0.07447 0.06888 -0.0806 1.0000 0.0639
-12.000 -0.6064 0.07035 0.06471 -0.0810 1.0000 0.0636
-11.750 -0.6330 0.06640 0.06070 -0.0811 1.0000 0.0633
-11.500 -0.6580 0.06320 0.05744 -0.0803 1.0000 0.0630
-11.250 -0.6857 0.06065 0.05485 -0.0785 1.0000 0.0628
-11.000 -0.7156 0.05885 0.05303 -0.0755 1.0000 0.0626
-10.750 -0.7448 0.05712 0.05127 -0.0728 1.0000 0.0624
-10.500 -0.7680 0.05492 0.04895 -0.0714 1.0000 0.0623
-10.250 -0.7841 0.05283 0.04672 -0.0700 1.0000 0.0623
-10.000 -0.7676 0.04910 0.04250 -0.0755 0.9933 0.0633
-9.750 -0.7342 0.04564 0.03871 -0.0809 0.9840 0.0648
-9.500 -0.6967 0.04358 0.03666 -0.0843 0.9752 0.0672
-9.250 -0.6584 0.04140 0.03430 -0.0880 0.9665 0.0695
-9.000 -0.6189 0.03920 0.03179 -0.0915 0.9579 0.0723
-8.750 -0.5855 0.03753 0.03024 -0.0925 0.9480 0.0755
-8.500 -0.5489 0.03604 0.02872 -0.0948 0.9383 0.0812
-8.250 -0.5094 0.03455 0.02740 -0.0971 0.9305 0.0893
-8.000 -0.4799 0.03316 0.02614 -0.0979 0.9188 0.0998
-7.750 -0.4478 0.03139 0.02449 -0.1001 0.9082 0.1200
-7.500 -0.4092 0.02857 0.02211 -0.1057 0.9000 0.1604
-7.250 -0.3746 0.02554 0.01968 -0.1119 0.8881 0.2316
-7.000 -0.3202 0.02657 0.02127 -0.1152 0.8826 0.3255
-6.750 -0.2836 0.02935 0.02406 -0.1127 0.8703 0.3502
-6.500 -0.2265 0.03173 0.02629 -0.1138 0.8658 0.3712
-6.250 -0.1874 0.03423 0.02878 -0.1108 0.8547 0.3790
-6.000 -0.1303 0.03581 0.03020 -0.1123 0.8491 0.3940
-5.750 -0.0919 0.03632 0.03053 -0.1132 0.8372 0.4099
-5.500 -0.0306 0.03923 0.03339 -0.1105 0.8308 0.4136
-5.250 0.0002 0.03888 0.03287 -0.1118 0.8168 0.4296
-5.000 0.0526 0.04075 0.03463 -0.1092 0.8065 0.4355
-4.750 0.0852 0.04019 0.03388 -0.1106 0.7939 0.4505
-4.500 0.1014 0.03917 0.03269 -0.1118 0.7793 0.4661
-4.250 0.1399 0.04037 0.03381 -0.1079 0.7675 0.4721
-4.000 0.1637 0.03935 0.03259 -0.1096 0.7564 0.4864
-3.750 0.1860 0.03972 0.03291 -0.1063 0.7437 0.4944
-3.500 0.2561 0.04356 0.03667 -0.0987 0.7332 0.5614
-3.250 0.2743 0.04255 0.03554 -0.0982 0.7222 0.5653
-3.000 0.2424 0.03735 0.03014 -0.1073 0.7126 0.5229
-2.750 0.2677 0.03744 0.03015 -0.1047 0.7034 0.5295
-2.500 0.2855 0.03643 0.02902 -0.1063 0.6943 0.5353
-2.250 0.3085 0.03521 0.02765 -0.1090 0.6855 0.5409
-2.000 0.3295 0.03523 0.02762 -0.1064 0.6775 0.5456
-1.750 0.3504 0.03465 0.02697 -0.1066 0.6687 0.5498
-1.500 0.3833 0.03372 0.02582 -0.1102 0.6622 0.5535
-1.250 0.4074 0.03283 0.02484 -0.1135 0.6531 0.5570
-1.000 0.4365 0.03225 0.02414 -0.1144 0.6467 0.5595
-0.750 0.4557 0.03214 0.02403 -0.1131 0.6393 0.5622
-0.500 0.4799 0.03187 0.02370 -0.1132 0.6319 0.5653
-0.250 0.5159 0.03135 0.02300 -0.1159 0.6265 0.5674
0.000 0.5370 0.03119 0.02286 -0.1164 0.6190 0.5698
0.250 0.5699 0.03080 0.02234 -0.1190 0.6124 0.5728
0.500 0.6103 0.03035 0.02166 -0.1228 0.6072 0.5748
0.750 0.6321 0.03033 0.02169 -0.1234 0.5995 0.5767
1.000 0.6575 0.03026 0.02160 -0.1231 0.5939 0.5791
1.250 0.6908 0.03016 0.02138 -0.1244 0.5896 0.5817
1.500 0.7085 0.03045 0.02177 -0.1237 0.5826 0.5835
1.750 0.7374 0.03044 0.02172 -0.1247 0.5767 0.5855
2.000 0.7743 0.03029 0.02142 -0.1270 0.5722 0.5881
2.250 0.7959 0.03071 0.02189 -0.1271 0.5662 0.5911
2.500 0.8235 0.03099 0.02215 -0.1283 0.5603 0.5942
2.750 0.8550 0.03096 0.02206 -0.1293 0.5557 0.5965
3.000 0.8840 0.03116 0.02223 -0.1298 0.5514 0.5988
3.250 0.8967 0.03190 0.02313 -0.1282 0.5448 0.6009
3.500 0.9240 0.03217 0.02340 -0.1287 0.5400 0.6038
3.750 0.9596 0.03223 0.02337 -0.1304 0.5362 0.6076
4.000 0.9779 0.03308 0.02429 -0.1299 0.5308 0.6112
4.250 0.9948 0.03384 0.02514 -0.1290 0.5248 0.6143
4.500 1.0234 0.03401 0.02532 -0.1293 0.5205 0.6177
4.750 1.0596 0.03408 0.02533 -0.1308 0.5173 0.6216
5.000 1.0588 0.03576 0.02724 -0.1276 0.5111 0.6243
5.250 1.0763 0.03662 0.02816 -0.1269 0.5056 0.6281
5.500 1.1121 0.03665 0.02813 -0.1284 0.5018 0.6328
5.750 1.1502 0.03661 0.02806 -0.1298 0.4988 0.6381
6.000 1.1184 0.03988 0.03170 -0.1230 0.4912 0.6403
6.250 1.1383 0.04065 0.03252 -0.1225 0.4864 0.6459
6.500 1.1825 0.04022 0.03204 -0.1248 0.4832 0.6526
6.750 1.2278 0.03992 0.03170 -0.1271 0.4806 0.6596
7.000 1.0661 0.05061 0.04290 -0.1080 0.4674 0.6541
7.250 1.1480 0.04752 0.03978 -0.1129 0.4662 0.6644
7.500 1.2281 0.04525 0.03748 -0.1186 0.4645 0.6753
7.750 0.9856 0.06726 0.05980 -0.1025 0.4447 0.6618
8.000 1.0515 0.06306 0.05565 -0.1028 0.4447 0.6724
8.250 1.1281 0.05858 0.05118 -0.1044 0.4447 0.6867
8.500 1.2279 0.05319 0.04580 -0.1087 0.4450 0.7064
8.750 0.8740 0.09518 0.08800 -0.1046 0.4112 0.6698
9.000 0.8033 0.10756 0.10046 -0.1073 0.4036 0.6667
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