Eiffel 385 (S.T. Ae) (eiffel385-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 385 (S.T. Ae) (eiffel385-il) Reynolds number: 100,000 Max Cl/Cd: 52.46 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel385-il-100000.txt Download as CSV file: xf-eiffel385-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3108 0.09951 0.09446 -0.0292 1.0000 0.1697
-11.000 -0.3427 0.09903 0.09413 -0.0279 1.0000 0.1732
-10.750 -0.4586 0.08861 0.08393 -0.0325 1.0000 0.1325
-10.500 -0.4599 0.08677 0.08216 -0.0291 1.0000 0.1333
-10.250 -0.4656 0.08536 0.08081 -0.0262 1.0000 0.1339
-10.000 -0.4502 0.08327 0.07873 -0.0266 0.9967 0.1357
-9.750 -0.4438 0.06800 0.06330 -0.0475 0.9832 0.1262
-9.500 -0.4538 0.03962 0.03359 -0.0782 0.9694 0.1358
-9.250 -0.4217 0.03689 0.03042 -0.0817 0.9590 0.1473
-9.000 -0.3767 0.03980 0.03372 -0.0819 0.9505 0.1540
-8.750 -0.3383 0.03867 0.03240 -0.0849 0.9418 0.1648
-8.500 -0.3077 0.03663 0.02996 -0.0875 0.9313 0.1767
-8.250 -0.2633 0.03741 0.03084 -0.0895 0.9249 0.1866
-8.000 -0.2344 0.03705 0.03044 -0.0900 0.9142 0.1950
-7.750 -0.1940 0.03479 0.02763 -0.0941 0.9081 0.2075
-7.500 -0.1660 0.03519 0.02831 -0.0933 0.8977 0.2125
-7.250 -0.1260 0.03329 0.02603 -0.0966 0.8920 0.2209
-7.000 -0.0985 0.03172 0.02419 -0.0975 0.8828 0.2265
-6.750 -0.0608 0.03098 0.02345 -0.0991 0.8763 0.2318
-6.500 -0.0152 0.02925 0.02123 -0.1028 0.8727 0.2406
-6.250 0.0052 0.02851 0.02045 -0.1018 0.8617 0.2449
-6.000 0.0485 0.02766 0.01954 -0.1043 0.8572 0.2522
-5.750 0.0811 0.02671 0.01831 -0.1052 0.8502 0.2612
-5.500 0.1109 0.02629 0.01794 -0.1054 0.8420 0.2684
-5.250 0.1538 0.02525 0.01669 -0.1078 0.8379 0.2797
-5.000 0.1745 0.02517 0.01665 -0.1064 0.8276 0.2874
-4.750 0.2128 0.02456 0.01596 -0.1078 0.8221 0.2998
-4.500 0.2433 0.02430 0.01558 -0.1080 0.8146 0.3116
-4.250 0.2721 0.02402 0.01535 -0.1078 0.8064 0.3204
-4.000 0.3144 0.02337 0.01455 -0.1098 0.8019 0.3321
-3.750 0.3326 0.02345 0.01470 -0.1079 0.7907 0.3394
-3.500 0.3725 0.02289 0.01402 -0.1094 0.7852 0.3507
-3.250 0.3932 0.02293 0.01410 -0.1080 0.7747 0.3586
-3.000 0.4302 0.02245 0.01356 -0.1090 0.7683 0.3700
-2.750 0.4527 0.02251 0.01362 -0.1079 0.7585 0.3806
-2.500 0.4866 0.02210 0.01322 -0.1085 0.7514 0.3917
-2.250 0.5113 0.02209 0.01316 -0.1077 0.7422 0.4016
-2.000 0.5432 0.02171 0.01282 -0.1080 0.7343 0.4109
-1.750 0.5695 0.02164 0.01274 -0.1075 0.7255 0.4201
-1.500 0.6006 0.02135 0.01247 -0.1077 0.7170 0.4320
-1.250 0.6269 0.02123 0.01244 -0.1073 0.7079 0.4463
-1.000 0.6570 0.02093 0.01223 -0.1073 0.6992 0.4668
-0.750 0.6842 0.02080 0.01226 -0.1070 0.6895 0.4941
-0.500 0.7168 0.02030 0.01206 -0.1074 0.6808 0.5530
-0.250 0.7679 0.01938 0.01210 -0.1116 0.6696 1.0000
0.000 0.8020 0.01942 0.01189 -0.1123 0.6612 1.0000
0.250 0.8219 0.01987 0.01230 -0.1108 0.6493 1.0000
0.500 0.8522 0.02002 0.01230 -0.1108 0.6402 1.0000
0.750 0.8750 0.02036 0.01260 -0.1098 0.6287 1.0000
1.000 0.8989 0.02073 0.01292 -0.1089 0.6180 1.0000
1.250 0.9284 0.02089 0.01297 -0.1089 0.6080 1.0000
1.500 0.9480 0.02136 0.01346 -0.1074 0.5959 1.0000
1.750 0.9781 0.02155 0.01354 -0.1075 0.5866 1.0000
2.000 0.9983 0.02196 0.01399 -0.1061 0.5746 1.0000
2.250 1.0210 0.02235 0.01438 -0.1051 0.5636 1.0000
2.500 1.0496 0.02251 0.01446 -0.1050 0.5539 1.0000
2.750 1.0678 0.02303 0.01506 -0.1034 0.5423 1.0000
3.000 1.0983 0.02319 0.01512 -0.1036 0.5338 1.0000
3.250 1.1162 0.02363 0.01566 -0.1019 0.5220 1.0000
3.500 1.1387 0.02391 0.01595 -0.1009 0.5112 1.0000
3.750 1.1676 0.02391 0.01586 -0.1008 0.5013 1.0000
4.000 1.1847 0.02430 0.01634 -0.0990 0.4893 1.0000
4.250 1.2086 0.02441 0.01643 -0.0982 0.4783 1.0000
4.500 1.2350 0.02442 0.01637 -0.0977 0.4675 1.0000
4.750 1.2514 0.02477 0.01680 -0.0958 0.4553 1.0000
5.000 1.2721 0.02486 0.01688 -0.0944 0.4426 1.0000
5.250 1.2948 0.02488 0.01682 -0.0934 0.4299 1.0000
5.500 1.3144 0.02508 0.01702 -0.0920 0.4175 1.0000
5.750 1.3290 0.02550 0.01753 -0.0899 0.4054 1.0000
6.000 1.3477 0.02583 0.01786 -0.0885 0.3941 1.0000
6.250 1.3688 0.02609 0.01806 -0.0874 0.3824 1.0000
6.500 1.3789 0.02661 0.01872 -0.0847 0.3704 1.0000
6.750 1.3918 0.02706 0.01923 -0.0824 0.3583 1.0000
7.000 1.4048 0.02745 0.01962 -0.0802 0.3457 1.0000
7.250 1.4142 0.02787 0.02003 -0.0774 0.3320 1.0000
7.500 1.4123 0.02846 0.02075 -0.0728 0.3184 1.0000
7.750 1.4102 0.02915 0.02150 -0.0685 0.3033 1.0000
8.000 1.4052 0.03001 0.02240 -0.0641 0.2860 1.0000
8.250 1.3971 0.03117 0.02353 -0.0598 0.2660 1.0000
8.500 1.3831 0.03292 0.02533 -0.0555 0.2405 1.0000
8.750 1.3661 0.03532 0.02758 -0.0517 0.2119 1.0000
9.000 1.3500 0.03818 0.03020 -0.0487 0.1881 1.0000
9.250 1.3383 0.04116 0.03304 -0.0465 0.1684 1.0000
9.500 1.3312 0.04398 0.03572 -0.0448 0.1555 1.0000
9.750 1.3281 0.04658 0.03815 -0.0434 0.1460 1.0000
10.000 1.3307 0.04884 0.04044 -0.0423 0.1377 1.0000
10.250 1.3375 0.05075 0.04217 -0.0412 0.1310 1.0000
10.500 1.3443 0.05276 0.04427 -0.0403 0.1250 1.0000
10.750 1.3638 0.05382 0.04506 -0.0394 0.1188 1.0000
11.000 1.3699 0.05600 0.04746 -0.0387 0.1149 1.0000
11.250 1.3806 0.05781 0.04929 -0.0380 0.1103 1.0000
11.500 1.4074 0.05878 0.05010 -0.0375 0.1053 1.0000
11.750 1.4083 0.06140 0.05296 -0.0369 0.1024 1.0000
12.000 1.4157 0.06362 0.05529 -0.0364 0.0989 1.0000
12.250 1.4511 0.06448 0.05592 -0.0362 0.0939 1.0000
12.500 1.4433 0.06775 0.05949 -0.0356 0.0921 1.0000
12.750 1.4402 0.07092 0.06291 -0.0352 0.0900 1.0000
13.000 1.4386 0.07404 0.06622 -0.0350 0.0877 1.0000
13.250 1.4767 0.07500 0.06691 -0.0348 0.0831 1.0000
13.500 1.4579 0.07933 0.07157 -0.0347 0.0823 1.0000
13.750 1.4387 0.08409 0.07666 -0.0350 0.0815 1.0000
14.000 1.4194 0.08926 0.08213 -0.0358 0.0807 1.0000
14.250 1.3970 0.09507 0.08823 -0.0371 0.0800 1.0000
14.500 1.3717 0.10164 0.09508 -0.0392 0.0796 1.0000
14.750 1.3407 0.10946 0.10320 -0.0421 0.0795 1.0000
15.000 1.3004 0.11941 0.11346 -0.0467 0.0800 1.0000
15.250 1.2489 0.13254 0.12689 -0.0536 0.0812 1.0000
15.500 1.1900 0.14918 0.14373 -0.0627 0.0828 1.0000
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Polar data table (+)
Polar graphs
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