Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 428 (Bleriot) (eiffel428-il) Reynolds number: 500,000 Max Cl/Cd: 70.18 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel428-il-500000.txt Download as CSV file: xf-eiffel428-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 428 (Bleriot)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2692 0.09577 0.09365 -0.0368 1.0000 0.0261
-10.500 -0.2735 0.09210 0.09000 -0.0386 1.0000 0.0263
-10.250 -0.2762 0.08826 0.08619 -0.0399 1.0000 0.0264
-10.000 -0.2776 0.08457 0.08252 -0.0408 1.0000 0.0265
-9.750 -0.2791 0.08094 0.07893 -0.0413 1.0000 0.0265
-9.500 -0.2796 0.07474 0.07274 -0.0432 0.9973 0.0269
-9.250 -0.2591 0.07188 0.06988 -0.0440 0.9823 0.0276
-9.000 -0.2374 0.06768 0.06565 -0.0485 0.9597 0.0286
-8.750 -0.3499 0.07620 0.07415 -0.0467 0.9860 0.0270
-8.500 -0.3285 0.07389 0.07182 -0.0481 0.9696 0.0277
-8.250 -0.2914 0.06937 0.06725 -0.0571 0.9460 0.0288
-8.000 -0.2297 0.05869 0.05633 -0.0836 0.9204 0.0331
-7.750 -0.1999 0.05089 0.04818 -0.0940 0.8876 0.0333
-7.500 -0.1996 0.04366 0.04072 -0.0965 0.8614 0.0342
-7.250 -0.1844 0.04298 0.03992 -0.0954 0.8298 0.0348
-7.000 -0.1692 0.04158 0.03835 -0.0949 0.8036 0.0357
-6.750 -0.1535 0.03932 0.03588 -0.0949 0.7801 0.0370
-6.500 -0.1295 0.03668 0.03270 -0.0956 0.7634 0.0418
-6.250 -0.1123 0.03433 0.02996 -0.0950 0.7478 0.0421
-6.000 -0.1046 0.02759 0.02288 -0.0950 0.7383 0.0436
-5.750 -0.0838 0.02609 0.02130 -0.0945 0.7256 0.0445
-5.500 -0.0625 0.02481 0.01985 -0.0939 0.7106 0.0458
-5.250 -0.0405 0.02353 0.01836 -0.0933 0.6962 0.0477
-5.000 -0.0122 0.02477 0.01928 -0.0922 0.6800 0.0529
-4.750 0.0052 0.02116 0.01515 -0.0912 0.6678 0.0543
-4.500 0.0268 0.01916 0.01303 -0.0906 0.6505 0.0561
-4.250 0.0503 0.01816 0.01188 -0.0900 0.6285 0.0575
-4.000 0.0748 0.01596 0.00920 -0.0886 0.6108 0.0478
-3.750 0.0992 0.01495 0.00791 -0.0877 0.5865 0.0475
-3.500 0.1238 0.01399 0.00665 -0.0868 0.5606 0.0467
-3.250 0.1485 0.01337 0.00581 -0.0860 0.5326 0.0468
-3.000 0.1729 0.01294 0.00516 -0.0852 0.4981 0.0471
-2.750 0.1965 0.01269 0.00466 -0.0844 0.4525 0.0477
-2.500 0.2203 0.01249 0.00425 -0.0835 0.4126 0.0483
-2.250 0.2444 0.01242 0.00399 -0.0828 0.3731 0.0500
-2.000 0.2619 0.01306 0.00401 -0.0811 0.2127 0.0510
-1.750 0.2871 0.01288 0.00375 -0.0805 0.1970 0.0520
-1.500 0.3110 0.01292 0.00360 -0.0798 0.1405 0.0528
-1.250 0.3359 0.01269 0.00330 -0.0791 0.1364 0.0539
-1.000 0.3604 0.01237 0.00295 -0.0785 0.1325 0.0563
-0.750 0.3860 0.01223 0.00280 -0.0780 0.1303 0.0594
-0.500 0.4118 0.01216 0.00272 -0.0776 0.1289 0.0631
-0.250 0.4377 0.01213 0.00267 -0.0771 0.1277 0.0659
0.000 0.4632 0.01208 0.00261 -0.0766 0.1259 0.0727
0.250 0.4887 0.01206 0.00263 -0.0762 0.1246 0.0867
0.500 0.5068 0.01103 0.00281 -0.0748 0.1234 0.5176
0.750 0.5828 0.01024 0.00310 -0.0858 0.1201 1.0000
1.000 0.6070 0.01044 0.00326 -0.0851 0.1180 1.0000
1.250 0.6311 0.01065 0.00343 -0.0843 0.1163 1.0000
1.500 0.6553 0.01083 0.00358 -0.0836 0.1149 1.0000
1.750 0.6797 0.01101 0.00373 -0.0830 0.1129 1.0000
2.000 0.7037 0.01122 0.00393 -0.0823 0.1104 1.0000
2.250 0.7268 0.01150 0.00418 -0.0815 0.1074 1.0000
2.500 0.7483 0.01191 0.00457 -0.0804 0.1036 1.0000
2.750 0.7750 0.01188 0.00454 -0.0802 0.1005 1.0000
3.000 0.8004 0.01197 0.00459 -0.0798 0.0956 1.0000
3.250 0.8261 0.01203 0.00460 -0.0794 0.0899 1.0000
3.500 0.8513 0.01213 0.00454 -0.0790 0.0605 1.0000
3.750 0.8734 0.01248 0.00488 -0.0780 0.0526 1.0000
4.000 0.8947 0.01290 0.00533 -0.0768 0.0489 1.0000
4.250 0.9163 0.01329 0.00576 -0.0757 0.0462 1.0000
4.500 0.9382 0.01364 0.00615 -0.0747 0.0448 1.0000
4.750 0.9592 0.01406 0.00662 -0.0735 0.0426 1.0000
5.000 0.9788 0.01457 0.00717 -0.0721 0.0407 1.0000
5.250 0.9950 0.01531 0.00793 -0.0702 0.0385 1.0000
5.500 1.0079 0.01624 0.00891 -0.0677 0.0365 1.0000
5.750 1.0280 0.01664 0.00937 -0.0665 0.0351 1.0000
6.000 1.0452 0.01722 0.00998 -0.0648 0.0333 1.0000
6.250 1.0614 0.01785 0.01065 -0.0629 0.0316 1.0000
6.500 1.0743 0.01868 0.01148 -0.0606 0.0298 1.0000
6.750 1.0777 0.02014 0.01295 -0.0568 0.0283 1.0000
7.000 1.0949 0.02049 0.01338 -0.0551 0.0273 1.0000
7.250 1.1089 0.02112 0.01406 -0.0530 0.0260 1.0000
7.500 1.1224 0.02184 0.01482 -0.0509 0.0249 1.0000
7.750 1.1368 0.02242 0.01542 -0.0491 0.0235 1.0000
8.000 1.1481 0.02341 0.01642 -0.0470 0.0226 1.0000
8.250 1.1605 0.02499 0.01802 -0.0451 0.0215 1.0000
8.500 1.1758 0.02572 0.01884 -0.0435 0.0207 1.0000
8.750 1.1917 0.02670 0.01989 -0.0421 0.0198 1.0000
9.000 1.2075 0.02772 0.02096 -0.0408 0.0190 1.0000
9.250 1.2206 0.02861 0.02191 -0.0393 0.0183 1.0000
9.500 1.2302 0.02939 0.02274 -0.0377 0.0176 1.0000
9.750 1.2503 0.03144 0.02483 -0.0370 0.0166 1.0000
10.000 1.2625 0.03243 0.02596 -0.0354 0.0160 1.0000
10.250 1.2811 0.03406 0.02773 -0.0345 0.0153 1.0000
10.500 1.3011 0.03604 0.02986 -0.0337 0.0148 1.0000
10.750 1.3148 0.03786 0.03183 -0.0325 0.0144 1.0000
11.000 1.3254 0.03977 0.03388 -0.0311 0.0140 1.0000
11.250 1.3268 0.04072 0.03490 -0.0291 0.0137 1.0000
11.500 1.3318 0.04259 0.03690 -0.0275 0.0135 1.0000
11.750 1.3340 0.04432 0.03873 -0.0260 0.0132 1.0000
12.000 1.3339 0.04701 0.04156 -0.0246 0.0129 1.0000
12.250 1.3250 0.05171 0.04660 -0.0227 0.0126 1.0000
12.500 1.3191 0.05450 0.04960 -0.0213 0.0124 1.0000
12.750 1.3066 0.05888 0.05429 -0.0199 0.0122 1.0000
13.000 1.2932 0.06318 0.05881 -0.0191 0.0122 1.0000
13.250 1.2759 0.06795 0.06382 -0.0187 0.0121 1.0000
13.500 1.2566 0.07308 0.06917 -0.0189 0.0121 1.0000
13.750 1.2373 0.07837 0.07465 -0.0197 0.0121 1.0000
14.000 1.2174 0.08398 0.08043 -0.0211 0.0122 1.0000
14.250 1.1954 0.09031 0.08695 -0.0232 0.0122 1.0000
14.500 1.1745 0.09692 0.09370 -0.0260 0.0123 1.0000
14.750 1.1556 0.10358 0.10048 -0.0291 0.0125 1.0000
15.000 1.1315 0.11192 0.10900 -0.0336 0.0124 1.0000
15.250 1.1206 0.11800 0.11512 -0.0363 0.0127 1.0000
15.500 1.1022 0.12615 0.12342 -0.0413 0.0128 1.0000
15.750 1.0841 0.13507 0.13247 -0.0470 0.0129 1.0000
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Polar data table (+)
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