Eiffel 385 (S.T. Ae) (eiffel385-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 385 (S.T. Ae) (eiffel385-il) Reynolds number: 500,000 Max Cl/Cd: 93.49 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel385-il-500000-n5.txt Download as CSV file: xf-eiffel385-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -0.7628 0.08803 0.08445 -0.0704 1.0000 0.0290
-18.500 -0.7686 0.08396 0.08035 -0.0725 1.0000 0.0293
-18.250 -0.7761 0.07970 0.07604 -0.0747 1.0000 0.0296
-18.000 -0.7841 0.07557 0.07187 -0.0768 1.0000 0.0298
-17.750 -0.7924 0.07156 0.06782 -0.0787 1.0000 0.0300
-17.500 -0.8045 0.06720 0.06341 -0.0810 1.0000 0.0302
-17.250 -0.8179 0.06305 0.05921 -0.0829 1.0000 0.0303
-17.000 -0.8367 0.05849 0.05460 -0.0851 1.0000 0.0304
-16.750 -0.8614 0.05364 0.04971 -0.0871 1.0000 0.0305
-16.500 -0.8987 0.04835 0.04438 -0.0886 1.0000 0.0305
-16.250 -0.9486 0.03945 0.03536 -0.0965 0.9964 0.0303
-16.000 -0.9389 0.03067 0.02626 -0.1100 0.9899 0.0306
-15.750 -0.9161 0.02791 0.02332 -0.1136 0.9857 0.0310
-15.500 -0.8895 0.02607 0.02133 -0.1162 0.9828 0.0315
-15.250 -0.8671 0.02466 0.01979 -0.1170 0.9780 0.0319
-15.000 -0.8414 0.02342 0.01842 -0.1181 0.9739 0.0323
-14.750 -0.8140 0.02198 0.01691 -0.1196 0.9707 0.0329
-14.500 -0.7909 0.02089 0.01573 -0.1197 0.9649 0.0333
-14.250 -0.7640 0.01991 0.01467 -0.1203 0.9602 0.0339
-14.000 -0.7337 0.01905 0.01373 -0.1213 0.9573 0.0346
-13.750 -0.7072 0.01832 0.01292 -0.1214 0.9527 0.0353
-13.500 -0.6793 0.01764 0.01215 -0.1216 0.9478 0.0360
-13.250 -0.6477 0.01698 0.01140 -0.1225 0.9443 0.0366
-13.000 -0.6150 0.01638 0.01070 -0.1235 0.9408 0.0372
-12.750 -0.5886 0.01569 0.00996 -0.1234 0.9339 0.0381
-12.500 -0.5576 0.01505 0.00926 -0.1241 0.9288 0.0392
-12.250 -0.5263 0.01451 0.00865 -0.1247 0.9237 0.0403
-12.000 -0.4980 0.01406 0.00813 -0.1247 0.9163 0.0416
-11.750 -0.4665 0.01361 0.00760 -0.1252 0.9097 0.0432
-11.500 -0.4395 0.01314 0.00708 -0.1249 0.9010 0.0456
-11.250 -0.4103 0.01273 0.00661 -0.1250 0.8926 0.0485
-11.000 -0.3840 0.01232 0.00616 -0.1245 0.8835 0.0529
-10.750 -0.3565 0.01191 0.00573 -0.1242 0.8741 0.0602
-10.500 -0.3306 0.01159 0.00541 -0.1235 0.8631 0.0699
-10.250 -0.3034 0.01136 0.00516 -0.1231 0.8519 0.0792
-10.000 -0.2764 0.01118 0.00494 -0.1225 0.8393 0.0853
-9.750 -0.2496 0.01106 0.00474 -0.1219 0.8261 0.0901
-9.500 -0.2231 0.01092 0.00452 -0.1212 0.8113 0.0937
-9.250 -0.1970 0.01078 0.00431 -0.1204 0.7941 0.0974
-9.000 -0.1710 0.01070 0.00412 -0.1196 0.7757 0.1006
-8.750 -0.1451 0.01064 0.00394 -0.1188 0.7566 0.1027
-8.500 -0.1198 0.01057 0.00375 -0.1179 0.7366 0.1047
-8.250 -0.0949 0.01047 0.00355 -0.1169 0.7176 0.1076
-8.000 -0.0696 0.01038 0.00338 -0.1161 0.7009 0.1110
-7.750 -0.0438 0.01032 0.00324 -0.1153 0.6867 0.1142
-7.500 -0.0177 0.01028 0.00311 -0.1146 0.6746 0.1168
-7.000 0.0344 0.01008 0.00283 -0.1133 0.6553 0.1252
-6.750 0.0607 0.01003 0.00273 -0.1126 0.6471 0.1293
-6.500 0.0874 0.00995 0.00263 -0.1121 0.6400 0.1345
-6.250 0.1141 0.00987 0.00256 -0.1116 0.6332 0.1426
-6.000 0.1406 0.00985 0.00254 -0.1110 0.6268 0.1542
-5.750 0.1680 0.00982 0.00253 -0.1106 0.6206 0.1649
-5.500 0.1949 0.00984 0.00250 -0.1101 0.6129 0.1726
-5.250 0.2218 0.00986 0.00250 -0.1096 0.6056 0.1792
-5.000 0.2491 0.00987 0.00247 -0.1092 0.5986 0.1842
-4.750 0.2760 0.00988 0.00245 -0.1087 0.5930 0.1881
-4.500 0.3032 0.00988 0.00244 -0.1083 0.5881 0.1920
-4.250 0.3307 0.00988 0.00243 -0.1080 0.5830 0.1957
-4.000 0.3579 0.00990 0.00242 -0.1076 0.5776 0.1989
-3.500 0.4121 0.00989 0.00239 -0.1068 0.5674 0.2046
-3.250 0.4391 0.00988 0.00239 -0.1065 0.5621 0.2075
-3.000 0.4658 0.00990 0.00239 -0.1060 0.5566 0.2105
-2.750 0.4928 0.00991 0.00240 -0.1057 0.5511 0.2132
-2.500 0.5199 0.00992 0.00240 -0.1053 0.5452 0.2151
-2.250 0.5464 0.00995 0.00241 -0.1049 0.5393 0.2168
-2.000 0.5732 0.00997 0.00243 -0.1045 0.5333 0.2184
-1.750 0.5997 0.00996 0.00244 -0.1041 0.5261 0.2215
-1.500 0.6255 0.01000 0.00247 -0.1036 0.5194 0.2246
-1.250 0.6522 0.01000 0.00251 -0.1032 0.5121 0.2273
-1.000 0.6779 0.01005 0.00255 -0.1027 0.5037 0.2304
-0.750 0.7041 0.01010 0.00259 -0.1023 0.4950 0.2337
-0.500 0.7294 0.01017 0.00265 -0.1017 0.4862 0.2370
-0.250 0.7552 0.01021 0.00271 -0.1012 0.4771 0.2411
0.000 0.7799 0.01028 0.00279 -0.1006 0.4667 0.2468
0.250 0.8043 0.01039 0.00287 -0.0998 0.4534 0.2529
0.500 0.8279 0.01050 0.00298 -0.0990 0.4375 0.2635
0.750 0.8514 0.01063 0.00311 -0.0982 0.4222 0.2768
1.000 0.8747 0.01075 0.00327 -0.0974 0.4083 0.3036
1.250 0.8981 0.01088 0.00345 -0.0965 0.3960 0.3369
1.500 0.9210 0.01106 0.00362 -0.0957 0.3838 0.3576
1.750 0.9439 0.01124 0.00380 -0.0948 0.3700 0.3735
2.000 0.9658 0.01147 0.00399 -0.0937 0.3543 0.3871
2.250 0.9882 0.01166 0.00419 -0.0928 0.3426 0.3997
2.500 1.0100 0.01187 0.00439 -0.0918 0.3317 0.4121
2.750 1.0315 0.01208 0.00461 -0.0907 0.3199 0.4273
3.000 1.0528 0.01225 0.00483 -0.0896 0.3092 0.4519
3.250 1.0658 0.01192 0.00516 -0.0870 0.3001 0.7266
3.750 1.1509 0.01231 0.00588 -0.0942 0.2722 1.0000
4.000 1.1709 0.01263 0.00615 -0.0930 0.2601 1.0000
4.250 1.1896 0.01297 0.00644 -0.0915 0.2479 1.0000
4.500 1.2065 0.01334 0.00675 -0.0897 0.2348 1.0000
4.750 1.2235 0.01371 0.00706 -0.0879 0.2213 1.0000
5.000 1.2378 0.01419 0.00745 -0.0857 0.2035 1.0000
5.250 1.2510 0.01475 0.00791 -0.0834 0.1815 1.0000
5.500 1.2577 0.01563 0.00858 -0.0802 0.1468 1.0000
5.750 1.2632 0.01661 0.00937 -0.0769 0.1164 1.0000
6.000 1.2721 0.01746 0.01011 -0.0743 0.0965 1.0000
6.250 1.2811 0.01834 0.01090 -0.0718 0.0785 1.0000
6.500 1.2910 0.01919 0.01168 -0.0696 0.0674 1.0000
6.750 1.3031 0.01996 0.01243 -0.0678 0.0623 1.0000
7.000 1.3168 0.02065 0.01314 -0.0662 0.0600 1.0000
7.250 1.3299 0.02140 0.01392 -0.0647 0.0581 1.0000
7.500 1.3418 0.02225 0.01480 -0.0631 0.0562 1.0000
7.750 1.3527 0.02321 0.01578 -0.0616 0.0544 1.0000
8.000 1.3647 0.02413 0.01675 -0.0602 0.0532 1.0000
8.250 1.3768 0.02507 0.01775 -0.0590 0.0524 1.0000
8.500 1.3883 0.02609 0.01883 -0.0578 0.0516 1.0000
8.750 1.3986 0.02724 0.02004 -0.0566 0.0506 1.0000
9.000 1.4079 0.02850 0.02135 -0.0555 0.0495 1.0000
9.250 1.4153 0.02996 0.02285 -0.0544 0.0480 1.0000
9.500 1.4204 0.03169 0.02462 -0.0533 0.0467 1.0000
9.750 1.4275 0.03331 0.02629 -0.0524 0.0458 1.0000
10.000 1.4368 0.03479 0.02785 -0.0518 0.0450 1.0000
10.250 1.4449 0.03641 0.02955 -0.0512 0.0441 1.0000
10.500 1.4523 0.03815 0.03136 -0.0507 0.0433 1.0000
10.750 1.4580 0.04011 0.03338 -0.0503 0.0425 1.0000
11.000 1.4628 0.04220 0.03554 -0.0499 0.0417 1.0000
11.250 1.4661 0.04452 0.03792 -0.0496 0.0410 1.0000
11.500 1.4680 0.04701 0.04047 -0.0493 0.0403 1.0000
11.750 1.4672 0.04984 0.04337 -0.0491 0.0396 1.0000
12.000 1.4720 0.05210 0.04571 -0.0491 0.0390 1.0000
12.250 1.4755 0.05453 0.04823 -0.0490 0.0384 1.0000
12.500 1.4784 0.05705 0.05083 -0.0491 0.0376 1.0000
12.750 1.4806 0.05970 0.05356 -0.0492 0.0369 1.0000
13.000 1.4820 0.06247 0.05640 -0.0494 0.0362 1.0000
13.250 1.4822 0.06543 0.05943 -0.0496 0.0354 1.0000
13.500 1.4812 0.06858 0.06265 -0.0499 0.0347 1.0000
13.750 1.4781 0.07205 0.06618 -0.0504 0.0341 1.0000
14.000 1.4766 0.07537 0.06958 -0.0508 0.0335 1.0000
14.250 1.4766 0.07853 0.07284 -0.0513 0.0329 1.0000
14.500 1.4765 0.08172 0.07612 -0.0519 0.0319 1.0000
14.750 1.4740 0.08528 0.07976 -0.0526 0.0313 1.0000
15.000 1.4724 0.08876 0.08331 -0.0534 0.0304 1.0000
15.250 1.4692 0.09250 0.08712 -0.0542 0.0296 1.0000
15.500 1.4646 0.09649 0.09116 -0.0552 0.0289 1.0000
15.750 1.4616 0.10023 0.09500 -0.0562 0.0283 1.0000
16.000 1.4598 0.10383 0.09869 -0.0572 0.0273 1.0000
16.250 1.4564 0.10771 0.10265 -0.0584 0.0266 1.0000
16.500 1.4524 0.11175 0.10676 -0.0597 0.0258 1.0000
16.750 1.4478 0.11588 0.11095 -0.0611 0.0250 1.0000
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