EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 407 AIRFOIL (e407-il) Reynolds number: 200,000 Max Cl/Cd: 72.03 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e407-il-200000.txt Download as CSV file: xf-e407-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 407 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4151 0.09513 0.09226 -0.0460 0.9911 0.0540
-9.250 -0.4267 0.08784 0.08499 -0.0500 0.9887 0.0546
-9.000 -0.4519 0.07766 0.07480 -0.0566 0.9865 0.0551
-8.750 -0.4819 0.06921 0.06629 -0.0619 0.9843 0.0550
-8.500 -0.5114 0.06360 0.06059 -0.0640 0.9797 0.0547
-8.250 -0.5444 0.05940 0.05630 -0.0640 0.9745 0.0546
-8.000 -0.5640 0.05457 0.05129 -0.0669 0.9708 0.0548
-7.750 -0.6621 0.04949 0.04471 -0.0657 0.9731 0.0244
-7.500 -0.6440 0.04096 0.03497 -0.0685 0.9709 0.0194
-7.250 -0.6253 0.03942 0.03313 -0.0680 0.9664 0.0190
-7.000 -0.6010 0.03674 0.03010 -0.0688 0.9632 0.0189
-6.750 -0.5744 0.03292 0.02586 -0.0698 0.9610 0.0194
-6.500 -0.5444 0.03080 0.02354 -0.0708 0.9591 0.0198
-6.250 -0.5096 0.02998 0.02272 -0.0734 0.9574 0.0231
-6.000 -0.4921 0.02900 0.02163 -0.0719 0.9522 0.0251
-5.750 -0.4638 0.02816 0.02066 -0.0723 0.9492 0.0265
-5.500 -0.4333 0.02621 0.01874 -0.0738 0.9472 0.0315
-5.250 -0.3955 0.02514 0.01767 -0.0768 0.9454 0.0419
-5.000 -0.3517 0.02388 0.01648 -0.0813 0.9441 0.0685
-4.750 -0.3240 0.02230 0.01537 -0.0833 0.9398 0.1427
-4.500 -0.2746 0.02011 0.01489 -0.0910 0.9392 0.4739
-4.250 -0.2447 0.02049 0.01531 -0.0913 0.9355 0.5461
-4.000 -0.2114 0.02115 0.01590 -0.0920 0.9327 0.5780
-3.750 -0.1835 0.02190 0.01658 -0.0916 0.9291 0.6002
-3.500 -0.1645 0.02242 0.01706 -0.0896 0.9232 0.6150
-3.250 -0.1352 0.02307 0.01765 -0.0892 0.9199 0.6267
-3.000 -0.1007 0.02373 0.01825 -0.0899 0.9177 0.6377
-2.750 -0.0849 0.02396 0.01839 -0.0879 0.9106 0.6478
-2.500 -0.0585 0.02446 0.01889 -0.0869 0.9068 0.6545
-2.250 -0.0220 0.02478 0.01911 -0.0884 0.9045 0.6638
-2.000 -0.0086 0.02511 0.01945 -0.0854 0.8974 0.6695
-1.750 0.0236 0.02527 0.01954 -0.0864 0.8936 0.6780
-1.500 0.0552 0.02557 0.01982 -0.0864 0.8911 0.6841
-1.250 0.0785 0.02568 0.01986 -0.0862 0.8848 0.6918
-1.000 0.1054 0.02576 0.01993 -0.0858 0.8801 0.6953
-0.750 0.1436 0.02570 0.01981 -0.0880 0.8777 0.6994
-0.500 0.1904 0.02550 0.01950 -0.0925 0.8762 0.7049
-0.250 0.2037 0.02556 0.01958 -0.0900 0.8671 0.7072
0.000 0.2404 0.02541 0.01942 -0.0916 0.8642 0.7099
0.250 0.2822 0.02519 0.01917 -0.0944 0.8625 0.7133
0.500 0.3038 0.02523 0.01917 -0.0942 0.8536 0.7178
0.750 0.3436 0.02493 0.01886 -0.0966 0.8508 0.7206
1.000 0.3831 0.02461 0.01857 -0.0985 0.8489 0.7230
1.250 0.4021 0.02467 0.01865 -0.0973 0.8397 0.7261
1.500 0.4431 0.02428 0.01827 -0.0998 0.8370 0.7295
1.750 0.4909 0.02375 0.01773 -0.1038 0.8353 0.7335
2.000 0.5101 0.02371 0.01774 -0.1023 0.8260 0.7359
2.250 0.5504 0.02312 0.01721 -0.1042 0.8232 0.7384
2.500 0.5944 0.02243 0.01658 -0.1069 0.8215 0.7412
2.750 0.6195 0.02229 0.01648 -0.1067 0.8123 0.7449
3.000 0.6648 0.02149 0.01574 -0.1097 0.8097 0.7484
3.250 0.7089 0.02049 0.01484 -0.1120 0.8081 0.7507
3.500 0.7529 0.01951 0.01395 -0.1144 0.8055 0.7532
3.750 0.7795 0.01908 0.01361 -0.1139 0.7959 0.7565
4.000 0.8316 0.01794 0.01256 -0.1179 0.7933 0.7602
4.250 0.8586 0.01753 0.01223 -0.1175 0.7823 0.7633
4.500 0.8907 0.01690 0.01172 -0.1178 0.7719 0.7658
4.750 0.9265 0.01622 0.01114 -0.1187 0.7601 0.7688
5.000 0.9579 0.01577 0.01076 -0.1190 0.7436 0.7724
5.250 0.9986 0.01524 0.01025 -0.1212 0.7231 0.7764
5.500 1.0262 0.01497 0.01003 -0.1207 0.6955 0.7790
5.750 1.0541 0.01487 0.00987 -0.1203 0.6599 0.7819
6.000 1.0798 0.01499 0.00984 -0.1197 0.6158 0.7853
6.250 1.0991 0.01542 0.01003 -0.1181 0.5657 0.7894
6.500 1.1106 0.01601 0.01040 -0.1150 0.5181 0.7929
6.750 1.1178 0.01671 0.01093 -0.1113 0.4710 0.7963
7.000 1.1247 0.01752 0.01153 -0.1078 0.4240 0.8002
7.250 1.1321 0.01846 0.01223 -0.1047 0.3767 0.8043
7.500 1.1382 0.01936 0.01296 -0.1013 0.3334 0.8078
7.750 1.1452 0.02032 0.01375 -0.0982 0.2917 0.8118
8.000 1.1541 0.02137 0.01462 -0.0956 0.2506 0.8163
8.250 1.1633 0.02250 0.01555 -0.0933 0.2105 0.8204
8.500 1.1708 0.02366 0.01654 -0.0906 0.1747 0.8241
8.750 1.1807 0.02485 0.01762 -0.0885 0.1415 0.8285
9.000 1.1910 0.02621 0.01882 -0.0866 0.1127 0.8333
9.250 1.1973 0.02763 0.02013 -0.0839 0.0917 0.8376
9.500 1.2063 0.02903 0.02151 -0.0817 0.0746 0.8425
9.750 1.2155 0.03062 0.02308 -0.0798 0.0624 0.8477
10.000 1.2197 0.03240 0.02486 -0.0771 0.0546 0.8521
10.250 1.2314 0.03370 0.02629 -0.0754 0.0480 0.8576
10.500 1.2379 0.03572 0.02832 -0.0734 0.0429 0.8630
10.750 1.2488 0.03708 0.02984 -0.0716 0.0389 0.8691
11.000 1.2581 0.03886 0.03165 -0.0701 0.0353 0.8760
11.250 1.2673 0.04082 0.03377 -0.0682 0.0321 0.8823
11.500 1.2792 0.04244 0.03556 -0.0668 0.0294 0.8903
11.750 1.2865 0.04404 0.03725 -0.0649 0.0270 0.8992
12.000 1.2970 0.04678 0.04008 -0.0635 0.0242 0.9080
12.250 1.3017 0.04829 0.04185 -0.0612 0.0228 0.9245
12.500 1.3040 0.04997 0.04377 -0.0585 0.0215 1.0000
12.750 1.3147 0.05264 0.04661 -0.0581 0.0201 1.0000
13.000 1.3223 0.05532 0.04938 -0.0578 0.0188 1.0000
13.250 1.3257 0.06056 0.05486 -0.0571 0.0173 1.0000
13.500 1.3227 0.06335 0.05793 -0.0564 0.0167 1.0000
13.750 1.3191 0.06689 0.06174 -0.0559 0.0161 1.0000
14.000 1.3129 0.07106 0.06619 -0.0555 0.0156 1.0000
14.250 1.3033 0.07584 0.07125 -0.0555 0.0153 1.0000
14.500 1.2910 0.08110 0.07678 -0.0560 0.0150 1.0000
14.750 1.2761 0.08690 0.08286 -0.0570 0.0149 1.0000
15.000 1.2591 0.09328 0.08951 -0.0589 0.0149 1.0000
15.250 1.2402 0.10034 0.09683 -0.0617 0.0149 1.0000
15.500 1.2197 0.10812 0.10486 -0.0655 0.0150 1.0000
15.750 1.1981 0.11667 0.11365 -0.0703 0.0151 1.0000
16.000 1.1756 0.12611 0.12331 -0.0763 0.0154 1.0000
16.250 1.1525 0.13649 0.13389 -0.0834 0.0157 1.0000
16.500 1.1287 0.14798 0.14555 -0.0916 0.0161 1.0000
16.750 1.1026 0.16120 0.15889 -0.1010 0.0166 1.0000
17.000 1.0781 0.17470 0.17244 -0.1097 0.0173 1.0000
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Polar data table (+)
Polar graphs
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