Eiffel 430 (Lachassgne) (eiffel430-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 430 (Lachassgne) (eiffel430-il) Reynolds number: 50,000 Max Cl/Cd: 36.41 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel430-il-50000.txt Download as CSV file: xf-eiffel430-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 430 (Lachassgne)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2956 0.10983 0.10324 -0.0275 1.0000 0.1839
-9.750 -0.3068 0.10928 0.10283 -0.0276 1.0000 0.1873
-9.500 -0.3325 0.11031 0.10407 -0.0274 1.0000 0.1885
-9.250 -0.3039 0.10359 0.09735 -0.0259 1.0000 0.1923
-9.000 -0.3020 0.10116 0.09502 -0.0245 1.0000 0.1963
-8.750 -0.3126 0.09999 0.09399 -0.0228 1.0000 0.1999
-8.500 -0.3381 0.10019 0.09440 -0.0202 1.0000 0.2020
-8.250 -0.3700 0.10099 0.09541 -0.0172 1.0000 0.2030
-8.000 -0.4023 0.10202 0.09665 -0.0140 1.0000 0.2034
-7.750 -0.3990 0.09850 0.09325 -0.0114 0.9979 0.2052
-7.500 -0.3632 0.09336 0.08806 -0.0153 0.9880 0.2125
-7.250 -0.3383 0.08945 0.08410 -0.0262 0.9705 0.2201
-7.000 -0.3096 0.08514 0.07976 -0.0287 0.9597 0.2288
-6.750 -0.2866 0.08127 0.07584 -0.0342 0.9465 0.2379
-6.500 -0.2644 0.07810 0.07258 -0.0407 0.9334 0.2508
-6.250 -0.2401 0.07528 0.06965 -0.0462 0.9219 0.2658
-6.000 -0.2184 0.07093 0.06535 -0.0446 0.9132 0.2731
-5.750 -0.1927 0.06746 0.06183 -0.0480 0.9050 0.2890
-5.500 -0.1789 0.06491 0.05924 -0.0487 0.8938 0.3055
-5.250 -0.1550 0.06217 0.05642 -0.0514 0.8868 0.3375
-5.000 -0.1463 0.05961 0.05392 -0.0481 0.8767 0.3601
-4.250 -0.1137 0.05237 0.04685 -0.0374 0.8544 0.4908
-4.000 -0.1031 0.05000 0.04451 -0.0343 0.8469 0.5255
-3.750 -0.0944 0.04797 0.04246 -0.0323 0.8387 0.5458
-3.500 -0.0676 0.04559 0.03992 -0.0361 0.8335 0.5525
-3.250 0.0402 0.04274 0.03512 -0.0656 0.8231 0.2567
-3.000 0.0810 0.04011 0.03175 -0.0679 0.8183 0.2137
-2.750 0.1053 0.03852 0.02984 -0.0673 0.8128 0.2139
-2.500 0.1250 0.03736 0.02836 -0.0659 0.8060 0.2157
-2.250 0.1582 0.03568 0.02621 -0.0662 0.8011 0.2189
-2.000 0.1814 0.03428 0.02472 -0.0651 0.7940 0.2300
-1.750 0.2077 0.03291 0.02315 -0.0644 0.7874 0.2426
-1.500 0.2459 0.03107 0.02102 -0.0653 0.7826 0.2676
-1.250 0.2705 0.02996 0.01984 -0.0646 0.7756 0.2947
-1.000 0.3143 0.02860 0.01839 -0.0669 0.7696 0.3393
-0.750 0.3639 0.02724 0.01708 -0.0700 0.7650 0.3897
-0.500 0.3931 0.02676 0.01672 -0.0701 0.7565 0.4119
-0.250 0.4306 0.02588 0.01607 -0.0713 0.7505 0.4484
0.000 0.5437 0.02337 0.01498 -0.0866 0.7437 1.0000
0.250 0.5725 0.02343 0.01476 -0.0860 0.7338 1.0000
0.500 0.5992 0.02351 0.01461 -0.0850 0.7228 1.0000
0.750 0.6333 0.02331 0.01418 -0.0850 0.7130 1.0000
1.000 0.6578 0.02335 0.01407 -0.0835 0.6980 1.0000
1.250 0.6834 0.02340 0.01398 -0.0823 0.6829 1.0000
1.500 0.7099 0.02348 0.01393 -0.0812 0.6675 1.0000
1.750 0.7365 0.02360 0.01393 -0.0802 0.6509 1.0000
2.000 0.7625 0.02380 0.01402 -0.0792 0.6331 1.0000
2.250 0.7875 0.02411 0.01423 -0.0781 0.6143 1.0000
2.500 0.8115 0.02454 0.01455 -0.0769 0.5957 1.0000
2.750 0.8343 0.02502 0.01495 -0.0757 0.5772 1.0000
3.000 0.8560 0.02552 0.01539 -0.0743 0.5598 1.0000
3.250 0.8773 0.02601 0.01581 -0.0729 0.5439 1.0000
3.500 0.8996 0.02644 0.01617 -0.0716 0.5299 1.0000
3.750 0.9221 0.02679 0.01646 -0.0704 0.5167 1.0000
4.000 0.9393 0.02742 0.01714 -0.0686 0.5030 1.0000
4.250 0.9579 0.02794 0.01767 -0.0669 0.4902 1.0000
4.500 0.9783 0.02830 0.01801 -0.0654 0.4780 1.0000
4.750 1.0006 0.02850 0.01817 -0.0640 0.4661 1.0000
5.000 1.0191 0.02889 0.01858 -0.0623 0.4530 1.0000
5.250 1.0384 0.02933 0.01902 -0.0606 0.4406 1.0000
5.500 1.0600 0.02962 0.01924 -0.0592 0.4273 1.0000
5.750 1.0840 0.02997 0.01948 -0.0580 0.4132 1.0000
6.000 1.1131 0.03057 0.01981 -0.0577 0.3970 1.0000
6.250 1.1472 0.03210 0.02098 -0.0584 0.3762 1.0000
6.500 1.1820 0.03522 0.02376 -0.0599 0.3512 1.0000
6.750 1.2010 0.03894 0.02750 -0.0591 0.3312 1.0000
7.000 1.2119 0.04234 0.03107 -0.0571 0.3147 1.0000
7.250 1.2217 0.04560 0.03449 -0.0551 0.3011 1.0000
7.500 1.2331 0.04883 0.03783 -0.0533 0.2893 1.0000
7.750 1.2264 0.05130 0.04077 -0.0490 0.2807 1.0000
8.000 1.2301 0.05436 0.04402 -0.0465 0.2726 1.0000
8.250 1.2216 0.05720 0.04720 -0.0426 0.2660 1.0000
8.500 1.2285 0.06024 0.05032 -0.0407 0.2586 1.0000
8.750 1.2027 0.06368 0.05414 -0.0356 0.2553 1.0000
9.000 1.1769 0.06747 0.05818 -0.0312 0.2521 1.0000
9.250 1.1426 0.07180 0.06268 -0.0268 0.2507 1.0000
9.500 0.9764 0.08852 0.07955 -0.0258 0.2662 1.0000
9.750 0.9914 0.09094 0.08199 -0.0245 0.2586 1.0000
10.000 0.9502 0.10188 0.09293 -0.0283 0.2602 1.0000
10.250 0.7477 0.13861 0.12956 -0.0564 0.4119 1.0000
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Polar data table (+)
Polar graphs
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