EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 417 AIRFOIL (e417-il) Reynolds number: 500,000 Max Cl/Cd: 103.14 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e417-il-500000.txt Download as CSV file: xf-e417-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 417 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5458 0.02812 0.02238 -0.0868 0.9396 0.0191
-7.250 -0.5208 0.02573 0.01992 -0.0866 0.9387 0.0182
-7.000 -0.4943 0.02387 0.01793 -0.0866 0.9378 0.0174
-6.750 -0.4661 0.02250 0.01645 -0.0870 0.9370 0.0171
-6.500 -0.4368 0.02143 0.01531 -0.0878 0.9362 0.0170
-6.250 -0.4055 0.02052 0.01434 -0.0891 0.9355 0.0171
-6.000 -0.3921 0.01990 0.01367 -0.0870 0.9308 0.0175
-5.750 -0.3669 0.01920 0.01293 -0.0873 0.9280 0.0179
-5.500 -0.3356 0.01851 0.01218 -0.0888 0.9264 0.0183
-5.250 -0.3021 0.01793 0.01154 -0.0907 0.9252 0.0188
-5.000 -0.2664 0.01711 0.01066 -0.0933 0.9242 0.0204
-4.750 -0.2305 0.01664 0.01015 -0.0956 0.9234 0.0224
-4.500 -0.1942 0.01627 0.00972 -0.0978 0.9227 0.0246
-4.250 -0.1551 0.01546 0.00913 -0.1011 0.9222 0.0722
-4.000 -0.1049 0.01284 0.00817 -0.1096 0.9227 0.4734
-3.750 -0.0680 0.01275 0.00825 -0.1117 0.9220 0.5438
-3.500 -0.0315 0.01280 0.00825 -0.1136 0.9214 0.5659
-3.250 -0.0205 0.01300 0.00846 -0.1103 0.9141 0.5782
-3.000 0.0115 0.01314 0.00858 -0.1110 0.9121 0.5939
-2.750 0.0449 0.01345 0.00889 -0.1118 0.9105 0.6120
-2.500 0.0788 0.01349 0.00898 -0.1129 0.9094 0.6180
-2.250 0.1152 0.01343 0.00887 -0.1147 0.9086 0.6224
-1.750 0.1683 0.01340 0.00876 -0.1145 0.9012 0.6285
-1.500 0.2007 0.01327 0.00864 -0.1155 0.8989 0.6307
-1.250 0.2367 0.01308 0.00844 -0.1172 0.8974 0.6330
-1.000 0.2737 0.01286 0.00821 -0.1191 0.8962 0.6356
-0.750 0.3121 0.01259 0.00792 -0.1213 0.8953 0.6383
-0.500 0.3523 0.01226 0.00756 -0.1239 0.8945 0.6411
-0.250 0.3934 0.01184 0.00715 -0.1266 0.8940 0.6434
0.000 0.4100 0.01190 0.00723 -0.1243 0.8865 0.6453
0.250 0.4447 0.01163 0.00700 -0.1257 0.8846 0.6472
0.500 0.4814 0.01134 0.00674 -0.1275 0.8834 0.6495
0.750 0.5200 0.01101 0.00643 -0.1297 0.8822 0.6520
1.000 0.5633 0.01055 0.00598 -0.1328 0.8811 0.6546
1.250 0.6096 0.01009 0.00553 -0.1366 0.8798 0.6570
1.750 0.6632 0.00966 0.00520 -0.1360 0.8679 0.6610
2.000 0.7091 0.00930 0.00489 -0.1397 0.8651 0.6630
2.250 0.7237 0.00921 0.00483 -0.1367 0.8540 0.6651
2.500 0.7500 0.00906 0.00471 -0.1363 0.8441 0.6676
2.750 0.7846 0.00886 0.00454 -0.1377 0.8341 0.6703
3.000 0.8138 0.00876 0.00443 -0.1379 0.8197 0.6727
3.250 0.8420 0.00864 0.00433 -0.1378 0.7995 0.6746
3.500 0.8748 0.00859 0.00423 -0.1388 0.7715 0.6764
3.750 0.9025 0.00875 0.00423 -0.1386 0.7252 0.6785
4.250 0.9185 0.00988 0.00469 -0.1302 0.5931 0.6834
4.500 0.9237 0.01061 0.00508 -0.1257 0.5265 0.6859
4.750 0.9330 0.01133 0.00548 -0.1222 0.4638 0.6881
5.000 0.9454 0.01195 0.00587 -0.1194 0.4089 0.6900
5.250 0.9599 0.01257 0.00628 -0.1171 0.3580 0.6921
5.500 0.9753 0.01325 0.00672 -0.1150 0.3036 0.6944
5.750 0.9908 0.01400 0.00720 -0.1131 0.2485 0.6969
6.000 1.0068 0.01479 0.00771 -0.1113 0.1932 0.6994
6.250 1.0225 0.01566 0.00826 -0.1095 0.1378 0.7018
6.500 1.0376 0.01658 0.00888 -0.1077 0.0856 0.7039
6.750 1.0490 0.01782 0.00975 -0.1051 0.0299 0.7059
7.000 1.0666 0.01856 0.01047 -0.1035 0.0197 0.7081
7.250 1.0857 0.01915 0.01111 -0.1021 0.0175 0.7107
7.500 1.1030 0.01993 0.01196 -0.1004 0.0159 0.7134
7.750 1.1217 0.02058 0.01268 -0.0991 0.0153 0.7160
8.000 1.1394 0.02130 0.01347 -0.0976 0.0148 0.7184
8.250 1.1560 0.02203 0.01430 -0.0959 0.0142 0.7206
8.500 1.1715 0.02285 0.01520 -0.0941 0.0136 0.7229
8.750 1.1858 0.02376 0.01618 -0.0922 0.0130 0.7255
9.000 1.1982 0.02486 0.01736 -0.0900 0.0126 0.7283
9.250 1.2085 0.02618 0.01876 -0.0876 0.0124 0.7311
9.500 1.2176 0.02777 0.02044 -0.0851 0.0121 0.7336
9.750 1.2288 0.02932 0.02211 -0.0830 0.0120 0.7358
10.000 1.2435 0.03044 0.02336 -0.0813 0.0118 0.7383
10.250 1.2581 0.03176 0.02479 -0.0798 0.0117 0.7410
10.500 1.2730 0.03312 0.02627 -0.0783 0.0116 0.7439
10.750 1.2880 0.03463 0.02790 -0.0769 0.0115 0.7469
11.000 1.3029 0.03628 0.02970 -0.0755 0.0114 0.7496
11.250 1.3173 0.03810 0.03171 -0.0741 0.0113 0.7523
11.500 1.3307 0.04019 0.03399 -0.0726 0.0113 0.7552
11.750 1.3420 0.04258 0.03660 -0.0710 0.0113 0.7581
12.000 1.3501 0.04539 0.03966 -0.0692 0.0114 0.7609
12.250 1.3540 0.04870 0.04322 -0.0671 0.0116 0.7635
12.500 1.3528 0.05218 0.04698 -0.0647 0.0117 0.7658
12.750 1.3592 0.05708 0.05209 -0.0636 0.0121 0.7683
13.000 1.3535 0.05973 0.05494 -0.0611 0.0121 0.7713
13.250 1.3452 0.06277 0.05818 -0.0589 0.0121 0.7745
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Polar data table (+)
Polar graphs
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