Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 371 (Monge) (eiffel371-il) Reynolds number: 50,000 Max Cl/Cd: 19.9 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel371-il-50000.txt Download as CSV file: xf-eiffel371-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3178 0.11211 0.10543 -0.0219 1.0000 0.2930
-9.500 -0.3267 0.11016 0.10359 -0.0212 1.0000 0.3054
-9.250 -0.3414 0.10901 0.10258 -0.0201 1.0000 0.3195
-9.000 -0.3382 0.10638 0.10001 -0.0185 1.0000 0.3351
-8.750 -0.3275 0.10319 0.09687 -0.0168 1.0000 0.3507
-8.500 -0.3300 0.10099 0.09476 -0.0148 1.0000 0.3674
-8.250 -0.3106 0.09700 0.09080 -0.0129 1.0000 0.3874
-8.000 -0.3020 0.09413 0.08799 -0.0109 1.0000 0.4059
-7.750 -0.2980 0.09153 0.08547 -0.0088 1.0000 0.4237
-7.500 -0.2997 0.08920 0.08323 -0.0066 1.0000 0.4390
-6.000 -0.5756 0.05990 0.05379 -0.0131 1.0000 0.1670
-5.750 -0.5871 0.05517 0.04820 -0.0108 1.0000 0.1433
-5.500 -0.5797 0.05226 0.04514 -0.0086 1.0000 0.1367
-5.250 -0.5759 0.04929 0.04172 -0.0062 1.0000 0.1306
-5.000 -0.5705 0.04748 0.03903 -0.0031 1.0000 0.1255
-4.750 -0.5603 0.04542 0.03665 -0.0011 1.0000 0.1254
-4.500 -0.5485 0.04358 0.03446 0.0009 1.0000 0.1256
-4.250 -0.5350 0.04179 0.03233 0.0028 1.0000 0.1256
-4.000 -0.5199 0.04009 0.03033 0.0045 1.0000 0.1259
-3.750 -0.5039 0.03815 0.02836 0.0057 1.0000 0.1290
-3.500 -0.4669 0.03696 0.02692 0.0037 0.9929 0.1367
-3.250 -0.4187 0.03564 0.02530 0.0003 0.9828 0.1450
-3.000 -0.3743 0.03451 0.02417 -0.0025 0.9723 0.1629
-2.750 -0.3276 0.03346 0.02322 -0.0054 0.9625 0.1936
-2.500 -0.0482 0.03316 0.02573 -0.0373 0.9723 1.0000
-2.250 -0.0044 0.03338 0.02555 -0.0424 0.9576 1.0000
-2.000 0.0355 0.03362 0.02548 -0.0464 0.9431 1.0000
-1.750 0.0738 0.03389 0.02547 -0.0499 0.9285 1.0000
-1.500 0.1107 0.03417 0.02550 -0.0529 0.9141 1.0000
-1.250 0.1478 0.03443 0.02555 -0.0556 0.8996 1.0000
-1.000 0.1854 0.03467 0.02558 -0.0582 0.8855 1.0000
-0.750 0.2261 0.03485 0.02558 -0.0612 0.8718 1.0000
-0.500 0.2791 0.03479 0.02534 -0.0659 0.8595 1.0000
-0.250 0.3062 0.03509 0.02552 -0.0664 0.8450 1.0000
0.000 0.3332 0.03540 0.02574 -0.0668 0.8308 1.0000
0.250 0.3619 0.03570 0.02595 -0.0674 0.8169 1.0000
0.500 0.3962 0.03586 0.02602 -0.0687 0.8033 1.0000
0.750 0.4404 0.03574 0.02583 -0.0715 0.7906 1.0000
1.000 0.5041 0.03491 0.02491 -0.0767 0.7798 1.0000
1.250 0.5283 0.03516 0.02513 -0.0761 0.7650 1.0000
1.500 0.5508 0.03551 0.02544 -0.0752 0.7504 1.0000
1.750 0.5752 0.03578 0.02569 -0.0745 0.7358 1.0000
2.000 0.5999 0.03605 0.02595 -0.0738 0.7213 1.0000
2.250 0.6249 0.03634 0.02623 -0.0731 0.7073 1.0000
2.500 0.6556 0.03636 0.02624 -0.0730 0.6937 1.0000
2.750 0.7033 0.03562 0.02545 -0.0751 0.6818 1.0000
3.000 0.7181 0.03633 0.02620 -0.0729 0.6671 1.0000
3.250 0.7259 0.03739 0.02727 -0.0700 0.6523 1.0000
3.500 0.7312 0.03861 0.02853 -0.0668 0.6381 1.0000
3.750 0.7396 0.03971 0.02966 -0.0640 0.6248 1.0000
4.000 0.7637 0.04008 0.03006 -0.0631 0.6129 1.0000
4.250 0.7962 0.04002 0.03000 -0.0631 0.6012 1.0000
4.500 0.7735 0.04257 0.03263 -0.0568 0.5881 1.0000
4.750 0.7553 0.04491 0.03501 -0.0511 0.5762 1.0000
5.000 0.8066 0.04397 0.03408 -0.0531 0.5658 1.0000
5.250 0.7672 0.04719 0.03737 -0.0451 0.5545 1.0000
5.500 0.6671 0.05268 0.04281 -0.0310 0.5458 1.0000
5.750 0.7816 0.04903 0.03929 -0.0390 0.5328 1.0000
6.000 0.6036 0.05922 0.04927 -0.0206 0.5253 1.0000
6.250 0.6239 0.05982 0.04989 -0.0192 0.5147 1.0000
6.500 0.7351 0.05419 0.04443 -0.0229 0.5006 1.0000
6.750 0.6189 0.06376 0.05381 -0.0143 0.4906 1.0000
7.000 0.6195 0.06568 0.05573 -0.0122 0.4782 1.0000
7.250 0.6443 0.06576 0.05586 -0.0109 0.4655 1.0000
7.500 0.7264 0.06072 0.05097 -0.0107 0.4542 1.0000
7.750 0.6490 0.06990 0.06006 -0.0078 0.4418 1.0000
8.000 0.6413 0.07310 0.06327 -0.0065 0.4302 1.0000
8.250 0.6699 0.07317 0.06340 -0.0055 0.4195 1.0000
8.500 0.6732 0.07553 0.06579 -0.0045 0.4082 1.0000
8.750 0.6420 0.08152 0.07177 -0.0040 0.3978 1.0000
9.000 0.6572 0.08301 0.07331 -0.0032 0.3871 1.0000
9.250 0.6608 0.08581 0.07615 -0.0028 0.3776 1.0000
9.500 0.6462 0.09100 0.08135 -0.0031 0.3717 1.0000
9.750 0.6228 0.09731 0.08766 -0.0041 0.3694 1.0000
10.000 0.6109 0.10277 0.09315 -0.0051 0.3702 1.0000
10.250 0.6107 0.10751 0.09793 -0.0062 0.3730 1.0000
10.500 0.6214 0.11169 0.10217 -0.0072 0.3749 1.0000
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Polar data table (+)
Polar graphs
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