Eiffel 385 (S.T. Ae) (eiffel385-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 385 (S.T. Ae) (eiffel385-il) Reynolds number: 200,000 Max Cl/Cd: 76.02 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel385-il-200000.txt Download as CSV file: xf-eiffel385-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 385 (S.T. Ae)
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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7876 0.04595 0.04148 -0.0923 1.0000 0.0587
-14.250 -0.8138 0.04213 0.03741 -0.0914 1.0000 0.0588
-14.000 -0.8269 0.03886 0.03391 -0.0900 1.0000 0.0592
-13.750 -0.8264 0.03661 0.03154 -0.0883 1.0000 0.0597
-13.500 -0.8190 0.03516 0.03006 -0.0865 1.0000 0.0605
-13.250 -0.8108 0.03368 0.02849 -0.0849 1.0000 0.0613
-13.000 -0.8016 0.03218 0.02685 -0.0833 1.0000 0.0623
-12.750 -0.7908 0.03076 0.02525 -0.0819 1.0000 0.0636
-12.500 -0.7580 0.02880 0.02294 -0.0847 0.9958 0.0655
-12.250 -0.7250 0.02695 0.02081 -0.0870 0.9914 0.0674
-12.000 -0.6903 0.02604 0.01994 -0.0887 0.9864 0.0694
-11.750 -0.6519 0.02507 0.01883 -0.0912 0.9823 0.0720
-11.500 -0.6193 0.02392 0.01737 -0.0926 0.9760 0.0752
-11.250 -0.5814 0.02324 0.01680 -0.0946 0.9713 0.0788
-11.000 -0.5449 0.02249 0.01584 -0.0964 0.9662 0.0838
-10.750 -0.5114 0.02175 0.01514 -0.0975 0.9597 0.0887
-10.500 -0.4710 0.02097 0.01422 -0.0999 0.9558 0.0973
-10.250 -0.4387 0.02056 0.01365 -0.1006 0.9480 0.1065
-10.000 -0.4005 0.01990 0.01308 -0.1025 0.9429 0.1171
-9.750 -0.3577 0.01938 0.01260 -0.1052 0.9398 0.1267
-9.500 -0.3284 0.01892 0.01199 -0.1052 0.9305 0.1339
-9.250 -0.2858 0.01877 0.01192 -0.1076 0.9265 0.1414
-9.000 -0.2403 0.01835 0.01140 -0.1105 0.9239 0.1486
-8.750 -0.2083 0.01829 0.01139 -0.1108 0.9145 0.1538
-8.500 -0.1662 0.01790 0.01077 -0.1130 0.9099 0.1604
-8.250 -0.1214 0.01784 0.01087 -0.1157 0.9064 0.1666
-8.000 -0.0922 0.01783 0.01071 -0.1153 0.8945 0.1736
-7.750 -0.0503 0.01747 0.01040 -0.1175 0.8892 0.1793
-7.500 -0.0219 0.01722 0.01009 -0.1171 0.8762 0.1839
-7.250 0.0100 0.01680 0.00947 -0.1174 0.8650 0.1890
-7.000 0.0437 0.01624 0.00886 -0.1181 0.8550 0.1939
-6.750 0.0713 0.01600 0.00861 -0.1176 0.8413 0.1990
-6.500 0.1004 0.01575 0.00816 -0.1173 0.8289 0.2055
-6.250 0.1315 0.01526 0.00764 -0.1176 0.8187 0.2119
-6.000 0.1573 0.01511 0.00743 -0.1168 0.8054 0.2198
-5.750 0.1846 0.01481 0.00706 -0.1164 0.7940 0.2282
-5.500 0.2138 0.01465 0.00683 -0.1163 0.7843 0.2372
-5.250 0.2393 0.01443 0.00655 -0.1156 0.7727 0.2453
-5.000 0.2676 0.01432 0.00640 -0.1153 0.7635 0.2532
-4.750 0.2941 0.01422 0.00619 -0.1148 0.7531 0.2605
-4.500 0.3210 0.01407 0.00607 -0.1143 0.7434 0.2671
-4.250 0.3483 0.01404 0.00594 -0.1139 0.7337 0.2742
-4.000 0.3747 0.01394 0.00581 -0.1134 0.7241 0.2803
-3.750 0.4021 0.01389 0.00575 -0.1130 0.7156 0.2864
-3.500 0.4286 0.01390 0.00570 -0.1125 0.7071 0.2922
-3.250 0.4559 0.01384 0.00560 -0.1122 0.6990 0.2972
-3.000 0.4827 0.01384 0.00562 -0.1118 0.6913 0.3026
-2.750 0.5093 0.01386 0.00562 -0.1113 0.6832 0.3090
-2.500 0.5369 0.01389 0.00562 -0.1111 0.6760 0.3157
-2.250 0.5624 0.01393 0.00572 -0.1104 0.6676 0.3236
-2.000 0.5909 0.01401 0.00571 -0.1103 0.6607 0.3317
-1.750 0.6155 0.01403 0.00583 -0.1096 0.6524 0.3392
-1.500 0.6429 0.01409 0.00584 -0.1093 0.6448 0.3485
-1.250 0.6684 0.01411 0.00595 -0.1087 0.6370 0.3574
-1.000 0.6946 0.01412 0.00599 -0.1083 0.6290 0.3697
-0.750 0.7210 0.01416 0.00607 -0.1079 0.6215 0.3866
-0.500 0.7452 0.01410 0.00615 -0.1071 0.6128 0.4096
-0.250 0.7717 0.01404 0.00618 -0.1067 0.6055 0.4438
0.000 0.7932 0.01384 0.00630 -0.1055 0.5965 0.4931
0.250 0.8540 0.01293 0.00642 -0.1122 0.5870 1.0000
0.500 0.8771 0.01307 0.00654 -0.1112 0.5771 1.0000
0.750 0.9036 0.01326 0.00661 -0.1108 0.5691 1.0000
1.000 0.9262 0.01339 0.00676 -0.1097 0.5589 1.0000
1.250 0.9514 0.01356 0.00685 -0.1091 0.5499 1.0000
1.500 0.9743 0.01368 0.00697 -0.1081 0.5392 1.0000
1.750 0.9976 0.01383 0.00710 -0.1072 0.5286 1.0000
2.000 1.0217 0.01396 0.00713 -0.1064 0.5178 1.0000
2.250 1.0427 0.01408 0.00728 -0.1050 0.5048 1.0000
2.500 1.0647 0.01424 0.00741 -0.1039 0.4923 1.0000
2.750 1.0871 0.01443 0.00753 -0.1028 0.4804 1.0000
3.000 1.1087 0.01463 0.00769 -0.1017 0.4679 1.0000
3.250 1.1297 0.01486 0.00793 -0.1004 0.4550 1.0000
3.500 1.1510 0.01514 0.00816 -0.0993 0.4431 1.0000
3.750 1.1723 0.01544 0.00838 -0.0982 0.4314 1.0000
4.000 1.1920 0.01573 0.00866 -0.0968 0.4185 1.0000
4.250 1.2114 0.01604 0.00897 -0.0954 0.4058 1.0000
4.500 1.2300 0.01637 0.00926 -0.0939 0.3931 1.0000
4.750 1.2485 0.01676 0.00956 -0.0924 0.3812 1.0000
5.000 1.2667 0.01710 0.00995 -0.0908 0.3698 1.0000
5.250 1.2846 0.01749 0.01034 -0.0893 0.3590 1.0000
5.750 1.3174 0.01829 0.01116 -0.0857 0.3376 1.0000
6.000 1.3315 0.01872 0.01159 -0.0835 0.3273 1.0000
6.250 1.3437 0.01918 0.01203 -0.0811 0.3167 1.0000
6.500 1.3560 0.01961 0.01253 -0.0787 0.3056 1.0000
6.750 1.3667 0.02012 0.01307 -0.0761 0.2939 1.0000
7.000 1.3753 0.02072 0.01366 -0.0733 0.2806 1.0000
7.250 1.3825 0.02138 0.01434 -0.0705 0.2644 1.0000
7.500 1.3878 0.02219 0.01515 -0.0676 0.2426 1.0000
7.750 1.3863 0.02342 0.01627 -0.0641 0.2111 1.0000
8.000 1.3757 0.02538 0.01797 -0.0600 0.1678 1.0000
8.250 1.3626 0.02784 0.02016 -0.0562 0.1355 1.0000
8.500 1.3531 0.03032 0.02251 -0.0533 0.1196 1.0000
8.750 1.3485 0.03263 0.02479 -0.0511 0.1099 1.0000
9.000 1.3453 0.03497 0.02713 -0.0493 0.1039 1.0000
9.250 1.3452 0.03718 0.02939 -0.0480 0.0989 1.0000
9.500 1.3415 0.03979 0.03199 -0.0467 0.0953 1.0000
9.750 1.3430 0.04204 0.03429 -0.0457 0.0922 1.0000
10.000 1.3461 0.04419 0.03652 -0.0449 0.0890 1.0000
10.250 1.3476 0.04654 0.03891 -0.0442 0.0862 1.0000
10.500 1.3471 0.04908 0.04141 -0.0434 0.0837 1.0000
10.750 1.3517 0.05122 0.04363 -0.0429 0.0813 1.0000
11.000 1.3563 0.05338 0.04587 -0.0424 0.0789 1.0000
11.250 1.3604 0.05561 0.04814 -0.0421 0.0767 1.0000
11.500 1.3643 0.05784 0.05036 -0.0416 0.0746 1.0000
11.750 1.3715 0.05965 0.05215 -0.0409 0.0725 1.0000
12.000 1.3764 0.06191 0.05454 -0.0407 0.0706 1.0000
12.250 1.3815 0.06416 0.05687 -0.0405 0.0686 1.0000
12.500 1.3872 0.06631 0.05903 -0.0403 0.0666 1.0000
12.750 1.3987 0.06767 0.06031 -0.0396 0.0645 1.0000
13.000 1.4048 0.06984 0.06259 -0.0393 0.0628 1.0000
13.250 1.4072 0.07253 0.06543 -0.0394 0.0611 1.0000
13.500 1.4112 0.07502 0.06800 -0.0395 0.0594 1.0000
13.750 1.4184 0.07707 0.07005 -0.0395 0.0575 1.0000
14.000 1.4345 0.07808 0.07100 -0.0385 0.0553 1.0000
14.250 1.4304 0.08167 0.07481 -0.0392 0.0542 1.0000
14.500 1.4290 0.08499 0.07829 -0.0398 0.0528 1.0000
14.750 1.4292 0.08811 0.08152 -0.0404 0.0513 1.0000
15.000 1.4358 0.09033 0.08376 -0.0406 0.0499 1.0000
15.250 1.4509 0.09161 0.08498 -0.0399 0.0480 1.0000
15.500 1.4388 0.09645 0.09008 -0.0415 0.0473 1.0000
15.750 1.4292 0.10114 0.09500 -0.0430 0.0464 1.0000
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Polar data table (+)
Polar graphs
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