Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 371 (Monge) (eiffel371-il) Reynolds number: 50,000 Max Cl/Cd: 31.64 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel371-il-50000-n5.txt Download as CSV file: xf-eiffel371-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3880 0.09252 0.08582 -0.0519 1.0000 0.0479
-9.750 -0.3930 0.08871 0.08208 -0.0524 1.0000 0.0476
-9.500 -0.4039 0.08467 0.07811 -0.0534 1.0000 0.0472
-9.250 -0.4192 0.08107 0.07459 -0.0534 1.0000 0.0468
-9.000 -0.4380 0.07810 0.07168 -0.0523 1.0000 0.0465
-8.750 -0.4624 0.07557 0.06920 -0.0494 1.0000 0.0462
-8.500 -0.4846 0.07307 0.06671 -0.0461 1.0000 0.0459
-8.250 -0.5040 0.07038 0.06401 -0.0430 1.0000 0.0456
-8.000 -0.5214 0.06766 0.06123 -0.0397 1.0000 0.0454
-7.750 -0.5363 0.06494 0.05841 -0.0363 1.0000 0.0451
-7.500 -0.5492 0.06214 0.05547 -0.0329 1.0000 0.0450
-7.250 -0.5592 0.05937 0.05253 -0.0295 1.0000 0.0448
-7.000 -0.5662 0.05669 0.04963 -0.0262 1.0000 0.0447
-6.750 -0.5500 0.05252 0.04495 -0.0273 0.9914 0.0455
-6.500 -0.5283 0.04851 0.04027 -0.0285 0.9810 0.0470
-6.250 -0.5030 0.04509 0.03625 -0.0294 0.9711 0.0484
-6.000 -0.4736 0.04238 0.03327 -0.0308 0.9618 0.0499
-5.750 -0.4448 0.03999 0.03053 -0.0315 0.9513 0.0513
-5.500 -0.4126 0.03791 0.02811 -0.0325 0.9416 0.0543
-5.250 -0.3769 0.03595 0.02565 -0.0336 0.9323 0.0586
-5.000 -0.3443 0.03417 0.02375 -0.0344 0.9221 0.0622
-4.750 -0.3038 0.03268 0.02207 -0.0364 0.9144 0.0688
-4.500 -0.2710 0.03139 0.02068 -0.0369 0.9032 0.0767
-4.250 -0.2266 0.03012 0.01926 -0.0393 0.8967 0.0892
-3.750 -0.1650 0.02802 0.01723 -0.0400 0.8739 0.1353
-3.500 -0.1304 0.02635 0.01613 -0.0415 0.8656 0.2087
-3.250 -0.1239 0.02481 0.01613 -0.0377 0.8523 0.4485
-3.000 -0.0294 0.02486 0.01717 -0.0438 0.8531 0.6733
-2.750 -0.0728 0.02428 0.01630 -0.0327 0.8330 0.7687
-2.500 -0.0632 0.02431 0.01608 -0.0285 0.8196 0.8192
-2.250 0.0886 0.02531 0.01665 -0.0470 0.8216 0.9030
-2.000 0.1395 0.02520 0.01621 -0.0511 0.8121 0.9165
-1.750 0.1849 0.02506 0.01576 -0.0543 0.8015 0.9270
-1.500 0.2268 0.02495 0.01541 -0.0570 0.7891 0.9356
-1.250 0.2632 0.02484 0.01506 -0.0585 0.7773 0.9441
-1.000 0.3107 0.02454 0.01451 -0.0621 0.7658 0.9504
-0.750 0.3473 0.02443 0.01419 -0.0637 0.7524 0.9576
-0.500 0.3867 0.02431 0.01388 -0.0659 0.7384 0.9641
-0.250 0.4234 0.02425 0.01364 -0.0677 0.7250 0.9708
0.000 0.4646 0.02414 0.01336 -0.0703 0.7123 0.9774
0.250 0.5038 0.02405 0.01309 -0.0725 0.7003 0.9838
0.500 0.5397 0.02406 0.01299 -0.0744 0.6869 0.9891
0.750 0.5696 0.02418 0.01302 -0.0751 0.6742 0.9928
1.000 0.5996 0.02427 0.01301 -0.0758 0.6620 0.9956
1.500 0.6555 0.02456 0.01316 -0.0764 0.6379 1.0000
1.750 0.6762 0.02483 0.01339 -0.0753 0.6259 1.0000
2.000 0.6992 0.02501 0.01351 -0.0744 0.6147 1.0000
2.250 0.7198 0.02528 0.01375 -0.0733 0.6030 1.0000
2.500 0.7383 0.02560 0.01408 -0.0719 0.5910 1.0000
2.750 0.7592 0.02586 0.01430 -0.0708 0.5797 1.0000
3.000 0.7803 0.02610 0.01453 -0.0697 0.5686 1.0000
3.250 0.7968 0.02650 0.01497 -0.0679 0.5565 1.0000
3.500 0.8157 0.02682 0.01529 -0.0665 0.5452 1.0000
3.750 0.8367 0.02706 0.01552 -0.0654 0.5346 1.0000
4.000 0.8509 0.02753 0.01606 -0.0634 0.5225 1.0000
4.250 0.8679 0.02791 0.01646 -0.0617 0.5115 1.0000
4.750 0.8990 0.02872 0.01738 -0.0579 0.4896 1.0000
5.000 0.9146 0.02912 0.01781 -0.0561 0.4792 1.0000
5.250 0.9305 0.02946 0.01818 -0.0542 0.4688 1.0000
5.500 0.9393 0.02999 0.01883 -0.0513 0.4574 1.0000
5.750 0.9516 0.03032 0.01918 -0.0489 0.4465 1.0000
6.000 0.9648 0.03049 0.01934 -0.0464 0.4351 1.0000
6.250 0.9675 0.03097 0.01992 -0.0425 0.4228 1.0000
6.500 0.9726 0.03135 0.02034 -0.0389 0.4116 1.0000
6.750 0.9813 0.03153 0.02053 -0.0358 0.4010 1.0000
7.000 0.9821 0.03197 0.02103 -0.0316 0.3904 1.0000
7.250 0.9842 0.03242 0.02151 -0.0277 0.3808 1.0000
7.500 0.9930 0.03272 0.02181 -0.0248 0.3723 1.0000
7.750 0.9924 0.03340 0.02256 -0.0207 0.3634 1.0000
8.000 1.0064 0.03369 0.02280 -0.0187 0.3553 1.0000
8.250 1.0030 0.03457 0.02382 -0.0144 0.3465 1.0000
8.500 1.0165 0.03496 0.02416 -0.0124 0.3381 1.0000
8.750 1.0134 0.03591 0.02523 -0.0084 0.3292 1.0000
9.000 1.0256 0.03648 0.02578 -0.0065 0.3208 1.0000
9.250 1.0263 0.03755 0.02694 -0.0034 0.3119 1.0000
9.500 1.0357 0.03838 0.02780 -0.0015 0.3034 1.0000
9.750 1.0393 0.03954 0.02908 0.0009 0.2950 1.0000
10.000 1.0487 0.04058 0.03018 0.0025 0.2871 1.0000
10.250 1.0506 0.04206 0.03178 0.0046 0.2793 1.0000
10.500 1.0651 0.04300 0.03274 0.0056 0.2723 1.0000
10.750 1.0588 0.04517 0.03512 0.0079 0.2652 1.0000
11.000 1.0787 0.04586 0.03581 0.0083 0.2589 1.0000
11.250 1.0678 0.04862 0.03878 0.0104 0.2528 1.0000
11.500 1.0660 0.05087 0.04119 0.0117 0.2468 1.0000
11.750 1.0944 0.05100 0.04129 0.0116 0.2416 1.0000
12.000 1.0583 0.05621 0.04679 0.0136 0.2365 1.0000
12.250 1.0419 0.06029 0.05103 0.0142 0.2314 1.0000
12.500 1.0683 0.06027 0.05104 0.0145 0.2269 1.0000
12.750 1.0128 0.06917 0.06014 0.0140 0.2223 1.0000
13.000 0.9097 0.08708 0.07812 0.0094 0.2140 1.0000
13.250 0.9223 0.08863 0.07979 0.0095 0.2114 1.0000
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Polar data table (+)
Polar graphs
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