Eiffel 385 (S.T. Ae) (eiffel385-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 385 (S.T. Ae) (eiffel385-il) Reynolds number: 100,000 Max Cl/Cd: 55.24 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel385-il-100000-n5.txt Download as CSV file: xf-eiffel385-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4169 0.09142 0.08571 -0.0536 1.0000 0.0636
-13.500 -0.4174 0.08899 0.08333 -0.0534 1.0000 0.0642
-13.000 -0.7212 0.04427 0.03844 -0.0785 1.0000 0.0644
-12.750 -0.7172 0.04181 0.03588 -0.0789 0.9989 0.0654
-12.500 -0.6913 0.03879 0.03263 -0.0835 0.9927 0.0674
-12.250 -0.6678 0.03546 0.02892 -0.0874 0.9857 0.0699
-12.000 -0.6403 0.03324 0.02644 -0.0901 0.9798 0.0728
-11.750 -0.6100 0.03224 0.02539 -0.0918 0.9734 0.0759
-11.500 -0.5816 0.03016 0.02292 -0.0940 0.9671 0.0808
-11.250 -0.5510 0.02943 0.02220 -0.0951 0.9602 0.0846
-11.000 -0.5199 0.02790 0.02031 -0.0969 0.9545 0.0909
-10.750 -0.4913 0.02720 0.01962 -0.0975 0.9467 0.0960
-10.500 -0.4564 0.02600 0.01806 -0.0996 0.9418 0.1041
-10.250 -0.4294 0.02556 0.01767 -0.0995 0.9329 0.1097
-10.000 -0.3946 0.02458 0.01639 -0.1012 0.9273 0.1174
-9.750 -0.3648 0.02429 0.01617 -0.1014 0.9194 0.1229
-9.500 -0.3316 0.02357 0.01520 -0.1025 0.9127 0.1303
-9.250 -0.2921 0.02346 0.01519 -0.1044 0.9085 0.1367
-9.000 -0.2658 0.02301 0.01452 -0.1041 0.8977 0.1444
-8.750 -0.2274 0.02321 0.01483 -0.1055 0.8923 0.1509
-8.500 -0.1999 0.02276 0.01414 -0.1053 0.8817 0.1580
-8.250 -0.1638 0.02259 0.01399 -0.1064 0.8752 0.1624
-8.000 -0.1357 0.02216 0.01341 -0.1062 0.8644 0.1676
-7.750 -0.1006 0.02155 0.01262 -0.1073 0.8571 0.1727
-7.500 -0.0730 0.02126 0.01230 -0.1069 0.8457 0.1765
-7.000 -0.0108 0.02038 0.01114 -0.1075 0.8260 0.1878
-6.750 0.0208 0.02003 0.01073 -0.1079 0.8166 0.1932
-6.500 0.0508 0.01963 0.01010 -0.1080 0.8061 0.2003
-6.250 0.0797 0.01933 0.00983 -0.1079 0.7956 0.2057
-6.000 0.1113 0.01905 0.00943 -0.1082 0.7865 0.2136
-5.750 0.1387 0.01880 0.00909 -0.1079 0.7755 0.2204
-5.500 0.1701 0.01854 0.00879 -0.1082 0.7672 0.2272
-5.250 0.1971 0.01837 0.00848 -0.1078 0.7564 0.2344
-5.000 0.2268 0.01813 0.00823 -0.1079 0.7481 0.2403
-4.750 0.2542 0.01800 0.00807 -0.1075 0.7383 0.2468
-4.500 0.2834 0.01788 0.00781 -0.1075 0.7300 0.2542
-4.250 0.3104 0.01776 0.00773 -0.1071 0.7208 0.2602
-4.000 0.3389 0.01767 0.00759 -0.1069 0.7126 0.2671
-3.750 0.3660 0.01760 0.00746 -0.1066 0.7034 0.2733
-3.500 0.3938 0.01754 0.00741 -0.1063 0.6949 0.2801
-3.250 0.4206 0.01754 0.00735 -0.1058 0.6856 0.2894
-3.000 0.4478 0.01753 0.00738 -0.1055 0.6771 0.2976
-2.750 0.4744 0.01754 0.00735 -0.1050 0.6681 0.3061
-2.500 0.5021 0.01753 0.00735 -0.1048 0.6605 0.3126
-2.250 0.5281 0.01756 0.00738 -0.1043 0.6518 0.3201
-2.000 0.5570 0.01756 0.00735 -0.1042 0.6448 0.3280
-1.750 0.5817 0.01762 0.00747 -0.1035 0.6361 0.3368
-1.500 0.6095 0.01764 0.00749 -0.1033 0.6287 0.3464
-1.250 0.6348 0.01771 0.00760 -0.1027 0.6204 0.3581
-1.000 0.6618 0.01776 0.00766 -0.1024 0.6125 0.3724
-0.750 0.6885 0.01782 0.00776 -0.1021 0.6048 0.3891
-0.500 0.7141 0.01787 0.00788 -0.1016 0.5961 0.4080
-0.250 0.7413 0.01788 0.00795 -0.1014 0.5887 0.4316
0.000 0.7653 0.01789 0.00815 -0.1007 0.5794 0.4617
0.250 0.7919 0.01776 0.00824 -0.1004 0.5719 0.5198
0.750 0.8612 0.01724 0.00863 -0.1030 0.5529 1.0000
1.000 0.8837 0.01747 0.00886 -0.1020 0.5428 1.0000
1.250 0.9082 0.01769 0.00902 -0.1013 0.5341 1.0000
1.500 0.9309 0.01792 0.00925 -0.1003 0.5240 1.0000
1.750 0.9540 0.01816 0.00946 -0.0995 0.5142 1.0000
2.000 0.9773 0.01838 0.00967 -0.0986 0.5045 1.0000
2.250 0.9994 0.01866 0.00996 -0.0976 0.4942 1.0000
2.500 1.0230 0.01889 0.01013 -0.0968 0.4851 1.0000
2.750 1.0441 0.01920 0.01048 -0.0957 0.4738 1.0000
3.000 1.0661 0.01948 0.01075 -0.0947 0.4636 1.0000
3.250 1.0879 0.01978 0.01101 -0.0936 0.4534 1.0000
3.500 1.1080 0.02012 0.01138 -0.0924 0.4416 1.0000
3.750 1.1282 0.02045 0.01168 -0.0911 0.4300 1.0000
4.000 1.1479 0.02078 0.01195 -0.0898 0.4182 1.0000
4.250 1.1659 0.02118 0.01238 -0.0882 0.4058 1.0000
4.500 1.1845 0.02160 0.01282 -0.0868 0.3947 1.0000
4.750 1.2029 0.02203 0.01318 -0.0854 0.3843 1.0000
5.000 1.2188 0.02250 0.01368 -0.0836 0.3718 1.0000
5.250 1.2334 0.02299 0.01417 -0.0816 0.3590 1.0000
5.500 1.2462 0.02350 0.01467 -0.0793 0.3457 1.0000
5.750 1.2573 0.02405 0.01516 -0.0768 0.3334 1.0000
6.000 1.2680 0.02464 0.01580 -0.0744 0.3213 1.0000
6.250 1.2786 0.02528 0.01647 -0.0720 0.3098 1.0000
6.500 1.2889 0.02598 0.01716 -0.0697 0.2991 1.0000
6.750 1.2991 0.02671 0.01797 -0.0675 0.2882 1.0000
7.000 1.3084 0.02751 0.01883 -0.0653 0.2771 1.0000
7.250 1.3155 0.02843 0.01977 -0.0629 0.2651 1.0000
7.500 1.3209 0.02948 0.02085 -0.0606 0.2515 1.0000
7.750 1.3252 0.03067 0.02210 -0.0583 0.2363 1.0000
8.000 1.3272 0.03208 0.02351 -0.0560 0.2194 1.0000
8.250 1.3276 0.03372 0.02516 -0.0539 0.1992 1.0000
8.500 1.3243 0.03574 0.02713 -0.0518 0.1772 1.0000
8.750 1.3175 0.03823 0.02951 -0.0498 0.1549 1.0000
9.000 1.3091 0.04107 0.03225 -0.0482 0.1372 1.0000
9.250 1.3011 0.04410 0.03522 -0.0469 0.1245 1.0000
9.500 1.2934 0.04729 0.03839 -0.0460 0.1153 1.0000
9.750 1.2869 0.05051 0.04164 -0.0453 0.1083 1.0000
10.000 1.2809 0.05382 0.04499 -0.0449 0.1029 1.0000
10.250 1.2768 0.05702 0.04826 -0.0446 0.0981 1.0000
10.500 1.2713 0.06048 0.05176 -0.0445 0.0946 1.0000
10.750 1.2672 0.06384 0.05516 -0.0444 0.0917 1.0000
11.000 1.2667 0.06685 0.05828 -0.0444 0.0887 1.0000
11.250 1.2654 0.07001 0.06152 -0.0446 0.0859 1.0000
11.500 1.2637 0.07325 0.06481 -0.0448 0.0836 1.0000
11.750 1.2628 0.07636 0.06791 -0.0449 0.0815 1.0000
12.000 1.2663 0.07901 0.07069 -0.0451 0.0793 1.0000
12.250 1.2693 0.08174 0.07351 -0.0453 0.0771 1.0000
12.500 1.2722 0.08449 0.07633 -0.0456 0.0751 1.0000
12.750 1.2755 0.08718 0.07904 -0.0458 0.0732 1.0000
13.000 1.2813 0.08938 0.08120 -0.0459 0.0713 1.0000
13.250 1.2851 0.09216 0.08415 -0.0463 0.0695 1.0000
13.500 1.2888 0.09495 0.08705 -0.0468 0.0676 1.0000
13.750 1.2920 0.09778 0.08996 -0.0473 0.0657 1.0000
14.000 1.2967 0.10033 0.09252 -0.0478 0.0638 1.0000
14.250 1.3055 0.10208 0.09422 -0.0478 0.0620 1.0000
14.500 1.3041 0.10589 0.09824 -0.0490 0.0605 1.0000
14.750 1.3038 0.10949 0.10200 -0.0502 0.0589 1.0000
15.000 1.3048 0.11283 0.10547 -0.0513 0.0573 1.0000
15.250 1.3077 0.11578 0.10847 -0.0523 0.0557 1.0000
15.500 1.3191 0.11706 0.10966 -0.0523 0.0540 1.0000
15.750 1.3143 0.12156 0.11436 -0.0542 0.0529 1.0000
16.000 1.3050 0.12704 0.12009 -0.0567 0.0517 1.0000
16.250 1.2972 0.13228 0.12554 -0.0593 0.0505 1.0000
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Polar data table (+)
Polar graphs
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