Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 371 (Monge) (eiffel371-il) Reynolds number: 100,000 Max Cl/Cd: 47.89 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel371-il-100000.txt Download as CSV file: xf-eiffel371-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 371 (Monge)
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3597 0.10069 0.09602 -0.0375 1.0000 0.1227
-9.500 -0.4033 0.09720 0.09270 -0.0430 1.0000 0.1251
-9.250 -0.4369 0.09350 0.08911 -0.0452 1.0000 0.1254
-9.000 -0.3774 0.09082 0.08638 -0.0370 1.0000 0.1316
-8.750 -0.3856 0.08810 0.08374 -0.0364 1.0000 0.1349
-8.500 -0.4172 0.08488 0.08066 -0.0373 1.0000 0.1385
-8.250 -0.4615 0.08255 0.07844 -0.0357 1.0000 0.1395
-8.000 -0.5068 0.08066 0.07657 -0.0323 1.0000 0.1404
-7.750 -0.5512 0.07911 0.07493 -0.0287 1.0000 0.1411
-7.500 -0.5237 0.07458 0.07062 -0.0267 1.0000 0.1455
-7.250 -0.5281 0.07254 0.06864 -0.0235 1.0000 0.1490
-7.000 -0.5482 0.07042 0.06650 -0.0205 1.0000 0.1531
-6.500 -0.5732 0.06525 0.06129 -0.0158 0.9984 0.1630
-6.250 -0.5475 0.06084 0.05670 -0.0203 0.9879 0.1789
-6.000 -0.5306 0.04726 0.04064 -0.0229 0.9733 0.0809
-5.750 -0.5011 0.04114 0.03448 -0.0249 0.9657 0.0745
-5.500 -0.4675 0.03697 0.02952 -0.0259 0.9567 0.0709
-5.250 -0.4343 0.03441 0.02652 -0.0267 0.9455 0.0711
-5.000 -0.3930 0.03188 0.02353 -0.0287 0.9377 0.0715
-4.750 -0.3532 0.02988 0.02125 -0.0303 0.9277 0.0732
-4.500 -0.3139 0.02851 0.01962 -0.0319 0.9174 0.0787
-4.250 -0.2666 0.02652 0.01757 -0.0349 0.9108 0.0845
-4.000 -0.2289 0.02542 0.01640 -0.0362 0.9000 0.0942
-3.750 -0.1820 0.02378 0.01491 -0.0391 0.8939 0.1110
-3.500 -0.1535 0.02257 0.01394 -0.0390 0.8822 0.1383
-3.250 -0.1276 0.01966 0.01295 -0.0384 0.8765 0.4191
-3.000 -0.1193 0.01923 0.01257 -0.0340 0.8622 0.5870
-2.750 -0.0933 0.01902 0.01336 -0.0305 0.8528 0.7575
-2.500 -0.0691 0.01895 0.01314 -0.0277 0.8448 0.8319
-2.250 0.0661 0.01972 0.01367 -0.0438 0.8456 0.8860
-2.000 0.2187 0.02006 0.01362 -0.0645 0.8442 0.9269
-1.750 0.2705 0.01978 0.01312 -0.0687 0.8296 0.9402
-1.500 0.3288 0.01936 0.01249 -0.0744 0.8150 0.9503
-1.250 0.3767 0.01904 0.01199 -0.0783 0.8005 0.9599
-1.000 0.4164 0.01886 0.01163 -0.0806 0.7860 0.9687
-0.750 0.4639 0.01850 0.01110 -0.0846 0.7716 0.9761
-0.500 0.5051 0.01830 0.01073 -0.0874 0.7574 0.9840
-0.250 0.5478 0.01803 0.01030 -0.0906 0.7432 0.9907
0.000 0.5880 0.01782 0.00994 -0.0933 0.7298 0.9967
0.250 0.6206 0.01778 0.00977 -0.0945 0.7160 1.0000
0.500 0.6420 0.01796 0.00988 -0.0935 0.7026 1.0000
0.750 0.6639 0.01815 0.00999 -0.0925 0.6895 1.0000
1.000 0.6866 0.01834 0.01009 -0.0916 0.6771 1.0000
1.250 0.7104 0.01851 0.01015 -0.0909 0.6650 1.0000
1.500 0.7314 0.01873 0.01033 -0.0897 0.6518 1.0000
1.750 0.7522 0.01897 0.01054 -0.0885 0.6386 1.0000
2.000 0.7738 0.01920 0.01073 -0.0875 0.6257 1.0000
2.250 0.7962 0.01942 0.01088 -0.0865 0.6133 1.0000
2.500 0.8191 0.01962 0.01100 -0.0856 0.6007 1.0000
2.750 0.8388 0.01987 0.01124 -0.0843 0.5865 1.0000
3.000 0.8589 0.02013 0.01150 -0.0829 0.5725 1.0000
3.250 0.8792 0.02036 0.01170 -0.0817 0.5584 1.0000
3.500 0.8996 0.02057 0.01187 -0.0804 0.5445 1.0000
3.750 0.9204 0.02077 0.01200 -0.0792 0.5308 1.0000
4.000 0.9418 0.02093 0.01209 -0.0780 0.5175 1.0000
4.250 0.9605 0.02110 0.01224 -0.0765 0.5031 1.0000
4.500 0.9781 0.02130 0.01246 -0.0748 0.4888 1.0000
4.750 0.9959 0.02152 0.01272 -0.0732 0.4754 1.0000
5.000 1.0145 0.02176 0.01296 -0.0717 0.4631 1.0000
5.250 1.0350 0.02196 0.01309 -0.0706 0.4523 1.0000
5.500 1.0519 0.02222 0.01340 -0.0689 0.4402 1.0000
5.750 1.0684 0.02254 0.01380 -0.0671 0.4288 1.0000
6.000 1.0867 0.02281 0.01406 -0.0657 0.4182 1.0000
6.250 1.1048 0.02307 0.01430 -0.0642 0.4075 1.0000
6.500 1.1191 0.02346 0.01478 -0.0621 0.3962 1.0000
6.750 1.1352 0.02382 0.01516 -0.0604 0.3855 1.0000
7.000 1.1541 0.02414 0.01539 -0.0591 0.3751 1.0000
7.250 1.1653 0.02461 0.01598 -0.0565 0.3635 1.0000
7.500 1.1782 0.02511 0.01652 -0.0543 0.3523 1.0000
7.750 1.1934 0.02559 0.01696 -0.0525 0.3411 1.0000
8.000 1.2062 0.02610 0.01745 -0.0503 0.3294 1.0000
8.250 1.2133 0.02672 0.01818 -0.0471 0.3178 1.0000
8.500 1.2233 0.02737 0.01883 -0.0445 0.3069 1.0000
8.750 1.2400 0.02802 0.01934 -0.0431 0.2961 1.0000
9.000 1.2391 0.02872 0.02028 -0.0386 0.2867 1.0000
9.250 1.2521 0.02948 0.02099 -0.0366 0.2783 1.0000
9.500 1.2522 0.03018 0.02184 -0.0323 0.2709 1.0000
9.750 1.2691 0.03097 0.02254 -0.0311 0.2640 1.0000
10.000 1.2586 0.03165 0.02345 -0.0250 0.2590 1.0000
10.250 1.2612 0.03228 0.02415 -0.0212 0.2539 1.0000
10.500 1.2766 0.03306 0.02488 -0.0198 0.2483 1.0000
10.750 1.2682 0.03386 0.02589 -0.0145 0.2435 1.0000
11.000 1.2782 0.03434 0.02636 -0.0122 0.2373 1.0000
11.250 1.2831 0.03504 0.02710 -0.0093 0.2312 1.0000
11.500 1.2802 0.03583 0.02805 -0.0052 0.2261 1.0000
11.750 1.3069 0.03619 0.02823 -0.0059 0.2191 1.0000
12.000 1.2946 0.03730 0.02962 -0.0006 0.2156 1.0000
12.250 1.2925 0.03831 0.03080 0.0028 0.2111 1.0000
12.500 1.3194 0.03849 0.03077 0.0021 0.2043 1.0000
12.750 1.3029 0.03990 0.03249 0.0070 0.2008 1.0000
13.000 1.2983 0.04114 0.03391 0.0099 0.1964 1.0000
13.250 1.3241 0.04121 0.03379 0.0094 0.1900 1.0000
13.500 1.3119 0.04310 0.03597 0.0126 0.1873 1.0000
13.750 1.3007 0.04499 0.03813 0.0152 0.1836 1.0000
14.000 1.3049 0.04597 0.03916 0.0164 0.1788 1.0000
14.250 1.3134 0.04696 0.04014 0.0171 0.1741 1.0000
14.500 1.2954 0.04971 0.04318 0.0191 0.1709 1.0000
14.750 1.2877 0.05186 0.04548 0.0200 0.1666 1.0000
15.000 1.3050 0.05207 0.04557 0.0201 0.1609 1.0000
15.250 1.2860 0.05572 0.04954 0.0208 0.1587 1.0000
15.500 1.2694 0.05949 0.05355 0.0210 0.1560 1.0000
15.750 1.2663 0.06157 0.05568 0.0208 0.1505 1.0000
16.000 1.2624 0.06407 0.05823 0.0204 0.1457 1.0000
16.250 1.2387 0.06938 0.06382 0.0194 0.1431 1.0000
16.500 1.2208 0.07417 0.06878 0.0181 0.1392 1.0000
16.750 1.2220 0.07624 0.07080 0.0172 0.1322 1.0000
17.000 1.1944 0.08313 0.07794 0.0150 0.1301 1.0000
17.250 1.1637 0.09092 0.08597 0.0123 0.1286 1.0000
17.500 1.1195 0.10175 0.09701 0.0087 0.1307 1.0000
17.750 1.1399 0.10084 0.09604 0.0079 0.1180 1.0000
18.000 1.0981 0.11165 0.10705 0.0037 0.1181 1.0000
18.250 1.0485 0.12485 0.12035 -0.0011 0.1200 1.0000
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