EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 417 AIRFOIL (e417-il) Reynolds number: 500,000 Max Cl/Cd: 94.36 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e417-il-500000-n5.txt Download as CSV file: xf-e417-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5285 0.07987 0.07702 -0.0953 0.9813 0.0071
-13.250 -0.5488 0.07137 0.06838 -0.1013 0.9797 0.0071
-13.000 -0.5661 0.06438 0.06119 -0.1063 0.9782 0.0071
-12.750 -0.5818 0.05837 0.05499 -0.1104 0.9769 0.0071
-12.500 -0.5914 0.05349 0.04990 -0.1138 0.9757 0.0071
-12.250 -0.5944 0.04957 0.04579 -0.1168 0.9748 0.0070
-12.000 -0.6120 0.04610 0.04217 -0.1158 0.9707 0.0071
-11.750 -0.6191 0.04308 0.03901 -0.1161 0.9677 0.0072
-11.500 -0.6205 0.04005 0.03575 -0.1170 0.9656 0.0072
-11.250 -0.6111 0.03815 0.03377 -0.1185 0.9642 0.0074
-11.000 -0.6050 0.03529 0.03067 -0.1199 0.9629 0.0074
-10.750 -0.6125 0.03440 0.02973 -0.1162 0.9576 0.0076
-10.500 -0.6083 0.03285 0.02806 -0.1153 0.9544 0.0077
-10.250 -0.5983 0.03101 0.02604 -0.1153 0.9523 0.0078
-10.000 -0.5845 0.02939 0.02426 -0.1155 0.9508 0.0078
-9.750 -0.5662 0.02767 0.02234 -0.1161 0.9499 0.0079
-9.500 -0.5762 0.02695 0.02152 -0.1104 0.9426 0.0079
-9.250 -0.5583 0.02560 0.02002 -0.1102 0.9407 0.0081
-9.000 -0.5375 0.02438 0.01867 -0.1102 0.9394 0.0081
-8.750 -0.5149 0.02324 0.01741 -0.1104 0.9384 0.0083
-8.500 -0.4908 0.02218 0.01625 -0.1108 0.9376 0.0083
-8.250 -0.4653 0.02122 0.01519 -0.1115 0.9369 0.0086
-8.000 -0.4668 0.02077 0.01468 -0.1066 0.9308 0.0088
-7.750 -0.4478 0.02001 0.01385 -0.1059 0.9283 0.0089
-7.500 -0.4242 0.01922 0.01299 -0.1060 0.9268 0.0092
-7.250 -0.3992 0.01844 0.01216 -0.1065 0.9256 0.0094
-7.000 -0.3724 0.01772 0.01137 -0.1074 0.9247 0.0096
-6.750 -0.3437 0.01707 0.01067 -0.1085 0.9240 0.0098
-6.500 -0.3144 0.01627 0.00982 -0.1099 0.9234 0.0100
-6.250 -0.2843 0.01538 0.00889 -0.1117 0.9228 0.0108
-6.000 -0.2805 0.01521 0.00869 -0.1075 0.9161 0.0110
-5.750 -0.2528 0.01473 0.00818 -0.1083 0.9144 0.0117
-5.500 -0.2231 0.01427 0.00767 -0.1094 0.9132 0.0122
-5.250 -0.1920 0.01384 0.00719 -0.1107 0.9123 0.0127
-5.000 -0.1601 0.01347 0.00677 -0.1121 0.9115 0.0134
-4.750 -0.1276 0.01309 0.00635 -0.1135 0.9109 0.0144
-4.500 -0.0947 0.01274 0.00597 -0.1151 0.9103 0.0165
-4.250 -0.0604 0.01221 0.00556 -0.1172 0.9098 0.0415
-4.000 -0.0230 0.01120 0.00501 -0.1207 0.9095 0.1573
-3.750 0.0178 0.00989 0.00438 -0.1255 0.9093 0.3393
-3.500 0.0576 0.00906 0.00414 -0.1293 0.9091 0.5066
-3.250 0.0930 0.00896 0.00414 -0.1311 0.9086 0.5493
-3.000 0.1028 0.00919 0.00438 -0.1273 0.9015 0.5667
-2.750 0.1339 0.00919 0.00436 -0.1280 0.8997 0.5810
-2.500 0.1665 0.00910 0.00426 -0.1291 0.8983 0.5847
-2.250 0.2003 0.00899 0.00412 -0.1305 0.8972 0.5878
-2.000 0.2353 0.00886 0.00395 -0.1321 0.8961 0.5908
-1.750 0.2719 0.00873 0.00378 -0.1341 0.8952 0.5937
-1.500 0.2915 0.00877 0.00380 -0.1324 0.8902 0.5961
-1.250 0.3170 0.00872 0.00376 -0.1320 0.8860 0.5982
-1.000 0.3507 0.00858 0.00362 -0.1333 0.8836 0.6005
-0.750 0.3871 0.00842 0.00345 -0.1352 0.8817 0.6029
-0.500 0.4099 0.00840 0.00343 -0.1341 0.8759 0.6053
-0.250 0.4374 0.00832 0.00333 -0.1341 0.8703 0.6079
0.000 0.4741 0.00817 0.00316 -0.1360 0.8671 0.6103
0.250 0.4963 0.00819 0.00322 -0.1349 0.8612 0.6121
0.500 0.5241 0.00815 0.00321 -0.1350 0.8559 0.6141
0.750 0.5628 0.00800 0.00307 -0.1373 0.8519 0.6162
1.000 0.5850 0.00799 0.00308 -0.1361 0.8408 0.6184
1.250 0.6150 0.00792 0.00300 -0.1366 0.8293 0.6206
1.500 0.6477 0.00786 0.00293 -0.1376 0.8179 0.6229
1.750 0.6808 0.00782 0.00287 -0.1388 0.8027 0.6253
2.000 0.7156 0.00781 0.00280 -0.1403 0.7806 0.6271
2.250 0.7464 0.00791 0.00280 -0.1409 0.7486 0.6289
2.500 0.7690 0.00815 0.00288 -0.1398 0.7082 0.6307
2.750 0.7853 0.00848 0.00303 -0.1373 0.6671 0.6327
3.000 0.7991 0.00887 0.00324 -0.1344 0.6259 0.6350
3.250 0.8119 0.00933 0.00349 -0.1314 0.5814 0.6374
3.500 0.8229 0.00990 0.00381 -0.1280 0.5271 0.6395
3.750 0.8343 0.01054 0.00416 -0.1249 0.4671 0.6415
4.000 0.8492 0.01111 0.00451 -0.1226 0.4150 0.6431
4.250 0.8643 0.01176 0.00490 -0.1204 0.3571 0.6449
4.500 0.8790 0.01252 0.00533 -0.1182 0.2887 0.6469
4.750 0.8949 0.01331 0.00579 -0.1164 0.2228 0.6491
5.000 0.9140 0.01391 0.00619 -0.1150 0.1791 0.6514
5.250 0.9336 0.01449 0.00659 -0.1138 0.1428 0.6535
5.500 0.9527 0.01512 0.00703 -0.1125 0.1052 0.6555
5.750 0.9715 0.01577 0.00752 -0.1112 0.0728 0.6573
6.000 0.9903 0.01639 0.00802 -0.1098 0.0459 0.6591
6.250 1.0071 0.01721 0.00867 -0.1082 0.0170 0.6612
6.500 1.0269 0.01777 0.00922 -0.1069 0.0120 0.6633
6.750 1.0479 0.01821 0.00972 -0.1059 0.0108 0.6656
7.000 1.0687 0.01868 0.01025 -0.1049 0.0101 0.6678
7.250 1.0888 0.01919 0.01081 -0.1037 0.0095 0.6699
7.500 1.1082 0.01977 0.01145 -0.1025 0.0090 0.6719
7.750 1.1266 0.02042 0.01218 -0.1011 0.0086 0.6738
8.000 1.1447 0.02107 0.01292 -0.0997 0.0083 0.6759
8.250 1.1630 0.02171 0.01365 -0.0983 0.0081 0.6782
8.500 1.1801 0.02243 0.01445 -0.0968 0.0079 0.6806
8.750 1.1967 0.02318 0.01528 -0.0952 0.0077 0.6829
9.000 1.2128 0.02397 0.01615 -0.0936 0.0075 0.6851
9.250 1.2282 0.02481 0.01705 -0.0919 0.0072 0.6872
9.500 1.2428 0.02568 0.01803 -0.0902 0.0070 0.6892
9.750 1.2569 0.02661 0.01904 -0.0884 0.0067 0.6914
10.000 1.2695 0.02765 0.02017 -0.0865 0.0066 0.6938
10.250 1.2814 0.02876 0.02137 -0.0846 0.0064 0.6964
10.500 1.2923 0.02998 0.02268 -0.0826 0.0063 0.6988
10.750 1.3017 0.03134 0.02412 -0.0805 0.0062 0.7012
11.000 1.3094 0.03288 0.02577 -0.0782 0.0061 0.7033
11.250 1.3157 0.03463 0.02765 -0.0760 0.0059 0.7053
11.500 1.3212 0.03655 0.02970 -0.0737 0.0058 0.7074
11.750 1.3305 0.03804 0.03131 -0.0720 0.0058 0.7099
12.000 1.3387 0.03967 0.03307 -0.0703 0.0058 0.7126
12.250 1.3462 0.04138 0.03493 -0.0686 0.0057 0.7154
12.750 1.3574 0.04529 0.03914 -0.0653 0.0056 0.7203
13.000 1.3614 0.04747 0.04148 -0.0637 0.0055 0.7228
13.250 1.3639 0.04986 0.04404 -0.0622 0.0055 0.7254
13.500 1.3650 0.05246 0.04683 -0.0609 0.0054 0.7280
13.750 1.3647 0.05532 0.04986 -0.0598 0.0053 0.7306
14.250 1.3596 0.06187 0.05678 -0.0582 0.0052 0.7358
14.500 1.3547 0.06563 0.06074 -0.0578 0.0052 0.7386
14.750 1.3482 0.06980 0.06511 -0.0579 0.0052 0.7415
15.000 1.3402 0.07438 0.06988 -0.0584 0.0051 0.7443
15.250 1.3307 0.07942 0.07513 -0.0595 0.0051 0.7470
15.500 1.3197 0.08495 0.08085 -0.0611 0.0051 0.7495
15.750 1.3074 0.09100 0.08711 -0.0634 0.0051 0.7518
16.000 1.2937 0.09765 0.09396 -0.0664 0.0051 0.7543
16.250 1.2792 0.10482 0.10133 -0.0700 0.0051 0.7567
16.500 1.2634 0.11257 0.10928 -0.0743 0.0051 0.7590
16.750 1.2472 0.12080 0.11770 -0.0792 0.0051 0.7612
17.000 1.2290 0.12993 0.12702 -0.0850 0.0051 0.7631
17.250 1.2112 0.13936 0.13663 -0.0912 0.0051 0.7650
17.500 1.1921 0.14962 0.14707 -0.0980 0.0052 0.7667
17.750 1.1705 0.16106 0.15868 -0.1057 0.0052 0.7681
18.000 1.1463 0.17400 0.17178 -0.1143 0.0053 0.7690
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