Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 371 (Monge) (eiffel371-il) Reynolds number: 100,000 Max Cl/Cd: 42.62 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel371-il-100000-n5.txt Download as CSV file: xf-eiffel371-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3703 0.09295 0.08814 -0.0457 1.0000 0.0278
-10.000 -0.3792 0.08845 0.08372 -0.0471 1.0000 0.0273
-9.750 -0.3924 0.08330 0.07865 -0.0491 1.0000 0.0269
-9.500 -0.4138 0.07666 0.07209 -0.0528 1.0000 0.0264
-9.250 -0.4443 0.07119 0.06664 -0.0544 1.0000 0.0258
-9.000 -0.4793 0.06770 0.06313 -0.0521 1.0000 0.0254
-8.750 -0.5148 0.06532 0.06073 -0.0470 1.0000 0.0251
-8.500 -0.5436 0.06133 0.05660 -0.0435 0.9989 0.0247
-8.250 -0.5480 0.05393 0.04871 -0.0459 0.9884 0.0242
-8.000 -0.5439 0.04852 0.04275 -0.0464 0.9790 0.0241
-7.750 -0.5303 0.04461 0.03842 -0.0467 0.9709 0.0242
-7.500 -0.5115 0.04159 0.03507 -0.0470 0.9629 0.0247
-7.250 -0.4922 0.03918 0.03236 -0.0468 0.9542 0.0256
-7.000 -0.4671 0.03656 0.02934 -0.0473 0.9474 0.0269
-6.750 -0.4471 0.03406 0.02637 -0.0463 0.9378 0.0281
-6.500 -0.4169 0.03137 0.02316 -0.0468 0.9317 0.0291
-6.250 -0.3907 0.02941 0.02079 -0.0462 0.9227 0.0298
-6.000 -0.3580 0.02751 0.01878 -0.0473 0.9165 0.0313
-5.750 -0.3273 0.02633 0.01752 -0.0478 0.9085 0.0338
-5.500 -0.2938 0.02502 0.01601 -0.0485 0.9005 0.0367
-5.250 -0.2612 0.02363 0.01451 -0.0490 0.8923 0.0389
-5.000 -0.2308 0.02260 0.01350 -0.0494 0.8828 0.0427
-4.750 -0.2038 0.02180 0.01259 -0.0489 0.8711 0.0478
-4.500 -0.1753 0.02084 0.01167 -0.0488 0.8607 0.0534
-4.250 -0.1471 0.02007 0.01089 -0.0486 0.8488 0.0634
-4.000 -0.1224 0.01936 0.01016 -0.0477 0.8346 0.0777
-3.750 -0.0970 0.01864 0.00951 -0.0471 0.8205 0.1053
-3.500 -0.0692 0.01787 0.00896 -0.0469 0.8071 0.1572
-3.250 -0.0455 0.01662 0.00871 -0.0462 0.7940 0.3447
-3.000 -0.0295 0.01611 0.00868 -0.0435 0.7800 0.4990
-2.750 -0.0062 0.01600 0.00829 -0.0423 0.7667 0.5624
-2.500 0.0200 0.01566 0.00783 -0.0416 0.7532 0.5931
-2.250 0.0490 0.01527 0.00745 -0.0414 0.7405 0.6174
-2.000 0.0973 0.01571 0.00859 -0.0423 0.7292 0.7333
-1.750 0.0893 0.01564 0.00809 -0.0361 0.7165 0.7764
-1.500 0.1076 0.01573 0.00800 -0.0336 0.7030 0.8035
-1.250 0.1316 0.01575 0.00787 -0.0323 0.6895 0.8203
-1.000 0.1609 0.01578 0.00773 -0.0322 0.6767 0.8285
-0.750 0.1879 0.01583 0.00757 -0.0318 0.6659 0.8336
-0.500 0.2164 0.01590 0.00752 -0.0317 0.6548 0.8382
-0.250 0.2427 0.01598 0.00745 -0.0313 0.6448 0.8429
0.000 0.2697 0.01606 0.00738 -0.0310 0.6354 0.8471
0.250 0.2975 0.01617 0.00741 -0.0310 0.6253 0.8506
0.500 0.3255 0.01628 0.00737 -0.0309 0.6165 0.8542
0.750 0.3489 0.01638 0.00740 -0.0301 0.6068 0.8576
1.000 0.3769 0.01650 0.00743 -0.0301 0.5980 0.8612
1.250 0.4052 0.01665 0.00752 -0.0301 0.5882 0.8661
1.500 0.4304 0.01678 0.00759 -0.0295 0.5792 0.8713
1.750 0.4594 0.01694 0.00770 -0.0297 0.5698 0.8756
2.000 0.4858 0.01710 0.00783 -0.0295 0.5601 0.8788
2.250 0.5112 0.01723 0.00788 -0.0292 0.5513 0.8804
2.500 0.5333 0.01737 0.00801 -0.0282 0.5413 0.8819
2.750 0.5574 0.01751 0.00806 -0.0276 0.5326 0.8834
3.000 0.5785 0.01764 0.00821 -0.0266 0.5224 0.8847
3.250 0.6010 0.01779 0.00832 -0.0258 0.5129 0.8856
3.500 0.6233 0.01793 0.00844 -0.0249 0.5028 0.8862
3.750 0.6452 0.01809 0.00861 -0.0241 0.4920 0.8868
4.000 0.6677 0.01824 0.00872 -0.0233 0.4814 0.8873
4.250 0.6891 0.01840 0.00889 -0.0224 0.4695 0.8883
4.500 0.7103 0.01858 0.00908 -0.0214 0.4571 0.8896
4.750 0.7309 0.01874 0.00925 -0.0203 0.4445 0.8907
5.000 0.7510 0.01892 0.00939 -0.0192 0.4321 0.8915
5.250 0.7706 0.01910 0.00956 -0.0181 0.4195 0.8922
5.500 0.7893 0.01931 0.00978 -0.0167 0.4058 0.8927
5.750 0.8078 0.01954 0.01000 -0.0155 0.3927 0.8932
6.000 0.8261 0.01980 0.01023 -0.0142 0.3801 0.8937
6.250 0.8442 0.02009 0.01049 -0.0129 0.3683 0.8942
6.500 0.8625 0.02041 0.01080 -0.0117 0.3576 0.8947
6.750 0.8810 0.02076 0.01117 -0.0106 0.3476 0.8953
7.000 0.8990 0.02113 0.01150 -0.0094 0.3385 0.8958
7.250 0.9169 0.02152 0.01197 -0.0082 0.3289 0.8965
7.500 0.9342 0.02192 0.01237 -0.0070 0.3209 0.8972
7.750 0.9509 0.02234 0.01286 -0.0057 0.3120 0.8983
8.000 0.9676 0.02281 0.01335 -0.0045 0.3041 0.8996
8.500 1.0010 0.02382 0.01451 -0.0022 0.2873 0.9036
8.750 1.0173 0.02437 0.01516 -0.0012 0.2786 0.9064
9.000 1.0338 0.02496 0.01582 -0.0003 0.2705 0.9096
9.250 1.0496 0.02559 0.01657 0.0007 0.2618 0.9130
9.500 1.0651 0.02628 0.01733 0.0015 0.2535 0.9167
9.750 1.0800 0.02701 0.01815 0.0023 0.2450 0.9217
10.000 1.0944 0.02781 0.01904 0.0031 0.2366 0.9282
10.250 1.1077 0.02867 0.01998 0.0039 0.2283 0.9378
10.500 1.1218 0.02960 0.02100 0.0044 0.2207 0.9501
10.750 1.1350 0.03056 0.02207 0.0048 0.2133 0.9828
11.000 1.1445 0.03160 0.02314 0.0061 0.2078 1.0000
11.250 1.1523 0.03267 0.02433 0.0076 0.2016 1.0000
11.500 1.1583 0.03381 0.02548 0.0091 0.1962 1.0000
11.750 1.1638 0.03508 0.02685 0.0104 0.1899 1.0000
12.000 1.1665 0.03649 0.02833 0.0117 0.1834 1.0000
12.250 1.1687 0.03806 0.02995 0.0129 0.1770 1.0000
12.500 1.1699 0.03981 0.03183 0.0138 0.1704 1.0000
12.750 1.1712 0.04162 0.03363 0.0146 0.1654 1.0000
13.000 1.1738 0.04354 0.03573 0.0151 0.1599 1.0000
13.250 1.1739 0.04567 0.03794 0.0155 0.1550 1.0000
13.500 1.1741 0.04790 0.04020 0.0158 0.1506 1.0000
13.750 1.1752 0.05022 0.04271 0.0158 0.1463 1.0000
14.000 1.1739 0.05280 0.04540 0.0158 0.1420 1.0000
14.500 1.1661 0.05886 0.05166 0.0150 0.1325 1.0000
14.750 1.1607 0.06225 0.05518 0.0144 0.1279 1.0000
15.000 1.1537 0.06586 0.05882 0.0136 0.1235 1.0000
15.250 1.1484 0.06955 0.06269 0.0127 0.1197 1.0000
15.500 1.1417 0.07356 0.06690 0.0116 0.1159 1.0000
15.750 1.1315 0.07810 0.07155 0.0101 0.1115 1.0000
16.000 1.1243 0.08227 0.07579 0.0088 0.1085 1.0000
16.250 1.1124 0.08751 0.08121 0.0070 0.1041 1.0000
16.500 1.1003 0.09290 0.08682 0.0050 0.0999 1.0000
16.750 1.0882 0.09837 0.09242 0.0029 0.0960 1.0000
17.000 1.0750 0.10421 0.09843 0.0006 0.0918 1.0000
17.250 1.0586 0.11079 0.10523 -0.0019 0.0879 1.0000
17.500 1.0397 0.11795 0.11258 -0.0048 0.0838 1.0000
17.750 1.0190 0.12560 0.12041 -0.0079 0.0812 1.0000
18.000 0.9932 0.13450 0.12948 -0.0115 0.0808 1.0000
18.250 0.9694 0.14322 0.13832 -0.0151 0.0808 1.0000
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