Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 428 (Bleriot) (eiffel428-il) Reynolds number: 200,000 Max Cl/Cd: 54.15 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel428-il-200000-n5.txt Download as CSV file: xf-eiffel428-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3495 0.09146 0.08801 -0.0375 1.0000 0.0237
-9.500 -0.3518 0.08803 0.08463 -0.0384 1.0000 0.0238
-9.250 -0.3581 0.08444 0.08112 -0.0393 1.0000 0.0240
-9.000 -0.3631 0.08106 0.07780 -0.0403 0.9984 0.0240
-8.750 -0.3557 0.07395 0.07072 -0.0495 0.9715 0.0246
-8.500 -0.3152 0.07303 0.06971 -0.0529 0.9399 0.0265
-8.250 -0.2840 0.06732 0.06390 -0.0638 0.9171 0.0286
-8.000 -0.2566 0.06015 0.05657 -0.0755 0.8937 0.0290
-7.750 -0.2358 0.05284 0.04903 -0.0849 0.8720 0.0298
-7.500 -0.2234 0.04237 0.03806 -0.0933 0.8524 0.0322
-7.250 -0.2025 0.04133 0.03692 -0.0938 0.8326 0.0330
-7.000 -0.1842 0.03843 0.03376 -0.0947 0.8166 0.0338
-6.750 -0.1660 0.03527 0.03028 -0.0953 0.8016 0.0347
-6.500 -0.1467 0.03262 0.02729 -0.0955 0.7868 0.0366
-6.250 -0.1276 0.02944 0.02361 -0.0954 0.7746 0.0378
-6.000 -0.1073 0.02687 0.02058 -0.0948 0.7630 0.0384
-5.750 -0.0856 0.02484 0.01809 -0.0941 0.7518 0.0391
-5.500 -0.0618 0.02394 0.01669 -0.0933 0.7393 0.0404
-5.250 -0.0404 0.02183 0.01426 -0.0927 0.7278 0.0412
-5.000 -0.0172 0.02052 0.01266 -0.0920 0.7141 0.0416
-4.750 0.0065 0.01948 0.01137 -0.0913 0.6985 0.0421
-4.500 0.0308 0.01863 0.01028 -0.0906 0.6831 0.0428
-4.250 0.0555 0.01788 0.00932 -0.0900 0.6687 0.0435
-4.000 0.0803 0.01722 0.00845 -0.0893 0.6516 0.0441
-3.750 0.1052 0.01663 0.00767 -0.0886 0.6327 0.0449
-3.500 0.1300 0.01620 0.00706 -0.0880 0.6124 0.0463
-3.250 0.1550 0.01580 0.00648 -0.0873 0.5893 0.0478
-3.000 0.1799 0.01537 0.00587 -0.0866 0.5670 0.0486
-2.750 0.2046 0.01496 0.00530 -0.0859 0.5427 0.0491
-2.500 0.2291 0.01464 0.00483 -0.0852 0.5179 0.0499
-2.250 0.2532 0.01442 0.00444 -0.0844 0.4894 0.0508
-2.000 0.2766 0.01433 0.00415 -0.0835 0.4537 0.0515
-1.750 0.2989 0.01411 0.00374 -0.0825 0.4158 0.0530
-1.500 0.3220 0.01401 0.00351 -0.0817 0.3824 0.0548
-1.250 0.3372 0.01488 0.00366 -0.0797 0.2183 0.0567
-1.000 0.3617 0.01488 0.00358 -0.0791 0.2015 0.0600
-0.750 0.3869 0.01487 0.00350 -0.0786 0.1883 0.0638
-0.500 0.4104 0.01498 0.00344 -0.0779 0.1384 0.0678
-0.250 0.4353 0.01496 0.00338 -0.0774 0.1349 0.0734
0.000 0.4602 0.01496 0.00337 -0.0768 0.1318 0.0835
0.250 0.4834 0.01457 0.00345 -0.0762 0.1304 0.2399
0.750 0.5700 0.01314 0.00379 -0.0834 0.1269 1.0000
1.000 0.5942 0.01335 0.00395 -0.0827 0.1247 1.0000
1.250 0.6177 0.01361 0.00416 -0.0820 0.1216 1.0000
1.500 0.6408 0.01391 0.00441 -0.0811 0.1185 1.0000
1.750 0.6639 0.01420 0.00466 -0.0803 0.1156 1.0000
2.000 0.6878 0.01443 0.00488 -0.0797 0.1136 1.0000
2.250 0.7115 0.01466 0.00511 -0.0790 0.1122 1.0000
2.500 0.7349 0.01492 0.00537 -0.0782 0.1104 1.0000
2.750 0.7578 0.01522 0.00568 -0.0774 0.1084 1.0000
3.000 0.7799 0.01557 0.00603 -0.0765 0.1062 1.0000
3.250 0.8018 0.01593 0.00639 -0.0756 0.1038 1.0000
3.500 0.8265 0.01607 0.00656 -0.0751 0.0998 1.0000
3.750 0.8496 0.01633 0.00682 -0.0744 0.0949 1.0000
4.000 0.8742 0.01646 0.00699 -0.0738 0.0903 1.0000
4.250 0.8988 0.01660 0.00726 -0.0733 0.0637 1.0000
4.500 0.9200 0.01699 0.00742 -0.0723 0.0561 1.0000
4.750 0.9403 0.01745 0.00793 -0.0711 0.0533 1.0000
5.000 0.9591 0.01801 0.00854 -0.0697 0.0505 1.0000
5.250 0.9760 0.01869 0.00928 -0.0681 0.0476 1.0000
5.500 0.9943 0.01925 0.00990 -0.0666 0.0460 1.0000
5.750 1.0122 0.01981 0.01057 -0.0651 0.0442 1.0000
6.000 1.0280 0.02049 0.01132 -0.0633 0.0418 1.0000
6.250 1.0412 0.02131 0.01221 -0.0612 0.0398 1.0000
6.500 1.0476 0.02243 0.01339 -0.0580 0.0380 1.0000
6.750 1.0620 0.02302 0.01406 -0.0560 0.0363 1.0000
7.000 1.0741 0.02377 0.01489 -0.0538 0.0342 1.0000
7.250 1.0842 0.02469 0.01589 -0.0514 0.0323 1.0000
7.500 1.0926 0.02577 0.01700 -0.0490 0.0305 1.0000
7.750 1.0993 0.02706 0.01832 -0.0466 0.0290 1.0000
8.000 1.1120 0.02796 0.01932 -0.0449 0.0274 1.0000
8.250 1.1229 0.02908 0.02052 -0.0432 0.0256 1.0000
8.500 1.1339 0.03020 0.02170 -0.0416 0.0241 1.0000
8.750 1.1447 0.03131 0.02285 -0.0402 0.0227 1.0000
9.000 1.1540 0.03276 0.02433 -0.0387 0.0216 1.0000
9.250 1.1669 0.03404 0.02573 -0.0373 0.0203 1.0000
9.500 1.1803 0.03545 0.02723 -0.0360 0.0192 1.0000
9.750 1.1927 0.03679 0.02867 -0.0348 0.0180 1.0000
10.000 1.2028 0.03810 0.03008 -0.0336 0.0171 1.0000
10.250 1.2114 0.03949 0.03155 -0.0326 0.0164 1.0000
10.500 1.2195 0.04120 0.03331 -0.0316 0.0156 1.0000
10.750 1.2338 0.04294 0.03525 -0.0304 0.0149 1.0000
11.000 1.2475 0.04494 0.03744 -0.0292 0.0143 1.0000
11.250 1.2585 0.04713 0.03983 -0.0280 0.0136 1.0000
11.500 1.2660 0.04945 0.04236 -0.0269 0.0131 1.0000
11.750 1.2703 0.05180 0.04489 -0.0259 0.0127 1.0000
12.000 1.2712 0.05393 0.04716 -0.0251 0.0123 1.0000
12.250 1.2716 0.05656 0.04996 -0.0244 0.0120 1.0000
12.500 1.2705 0.05893 0.05245 -0.0240 0.0117 1.0000
12.750 1.2679 0.06169 0.05533 -0.0238 0.0114 1.0000
13.000 1.2621 0.06520 0.05898 -0.0237 0.0111 1.0000
13.250 1.2543 0.06936 0.06343 -0.0236 0.0110 1.0000
13.500 1.2428 0.07411 0.06847 -0.0239 0.0108 1.0000
13.750 1.2289 0.07929 0.07391 -0.0246 0.0107 1.0000
14.000 1.2125 0.08502 0.07990 -0.0260 0.0106 1.0000
14.250 1.1949 0.09121 0.08633 -0.0280 0.0106 1.0000
14.500 1.1771 0.09775 0.09309 -0.0305 0.0106 1.0000
14.750 1.1584 0.10486 0.10041 -0.0338 0.0106 1.0000
15.000 1.1383 0.11275 0.10849 -0.0378 0.0106 1.0000
15.250 1.1180 0.12125 0.11717 -0.0426 0.0107 1.0000
15.500 1.0965 0.13076 0.12685 -0.0483 0.0107 1.0000
15.750 1.0768 0.14067 0.13690 -0.0544 0.0108 1.0000
16.000 1.0559 0.15208 0.14843 -0.0615 0.0110 1.0000
16.250 1.0329 0.16558 0.16200 -0.0693 0.0111 1.0000
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