Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 371 (Monge) (eiffel371-il) Reynolds number: 500,000 Max Cl/Cd: 69.72 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel371-il-500000-n5.txt Download as CSV file: xf-eiffel371-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6159 0.05631 0.05375 -0.0708 1.0000 0.0073
-12.000 -0.6575 0.04809 0.04534 -0.0760 1.0000 0.0072
-11.750 -0.6900 0.04414 0.04122 -0.0742 1.0000 0.0072
-11.500 -0.7102 0.03818 0.03483 -0.0766 0.9949 0.0073
-11.250 -0.7156 0.03440 0.03070 -0.0763 0.9878 0.0073
-11.000 -0.7128 0.03158 0.02755 -0.0752 0.9805 0.0074
-10.750 -0.7015 0.02892 0.02455 -0.0746 0.9748 0.0074
-10.500 -0.6889 0.02696 0.02232 -0.0734 0.9686 0.0076
-10.250 -0.6728 0.02502 0.02016 -0.0726 0.9638 0.0078
-10.000 -0.6481 0.02365 0.01863 -0.0729 0.9610 0.0079
-9.750 -0.6285 0.02270 0.01757 -0.0718 0.9544 0.0081
-9.500 -0.6023 0.02166 0.01640 -0.0720 0.9505 0.0083
-9.250 -0.5733 0.02062 0.01522 -0.0727 0.9473 0.0085
-9.000 -0.5487 0.01973 0.01421 -0.0723 0.9418 0.0087
-8.750 -0.5220 0.01881 0.01316 -0.0723 0.9360 0.0090
-8.500 -0.4909 0.01790 0.01212 -0.0731 0.9310 0.0093
-8.250 -0.4656 0.01714 0.01123 -0.0727 0.9235 0.0097
-8.000 -0.4363 0.01650 0.01047 -0.0730 0.9163 0.0100
-7.750 -0.4104 0.01580 0.00966 -0.0726 0.9084 0.0104
-7.500 -0.3849 0.01516 0.00896 -0.0722 0.8994 0.0109
-7.250 -0.3603 0.01467 0.00842 -0.0715 0.8896 0.0114
-7.000 -0.3348 0.01421 0.00788 -0.0709 0.8786 0.0118
-6.750 -0.3111 0.01379 0.00737 -0.0699 0.8652 0.0124
-6.500 -0.2878 0.01339 0.00687 -0.0688 0.8495 0.0130
-6.250 -0.2647 0.01304 0.00641 -0.0676 0.8306 0.0135
-6.000 -0.2431 0.01265 0.00592 -0.0662 0.8072 0.0145
-5.750 -0.2213 0.01241 0.00556 -0.0647 0.7791 0.0154
-5.500 -0.2002 0.01225 0.00525 -0.0631 0.7506 0.0165
-5.250 -0.1789 0.01211 0.00496 -0.0616 0.7251 0.0177
-5.000 -0.1583 0.01192 0.00464 -0.0599 0.7031 0.0191
-4.500 -0.1140 0.01165 0.00418 -0.0572 0.6691 0.0232
-4.250 -0.0918 0.01146 0.00395 -0.0560 0.6551 0.0268
-4.000 -0.0690 0.01134 0.00375 -0.0548 0.6409 0.0312
-3.750 -0.0466 0.01120 0.00356 -0.0535 0.6265 0.0379
-3.500 -0.0248 0.01103 0.00341 -0.0522 0.6122 0.0525
-3.250 -0.0025 0.01091 0.00328 -0.0510 0.5988 0.0729
-3.000 0.0204 0.01078 0.00315 -0.0499 0.5869 0.0902
-2.750 0.0432 0.01061 0.00305 -0.0489 0.5774 0.1165
-2.500 0.0652 0.01040 0.00293 -0.0477 0.5696 0.1554
-2.250 0.0838 0.00997 0.00279 -0.0459 0.5628 0.2385
-2.000 0.0975 0.00939 0.00271 -0.0433 0.5562 0.3872
-1.500 0.1403 0.00914 0.00279 -0.0405 0.5430 0.5110
-1.250 0.1666 0.00923 0.00281 -0.0401 0.5363 0.5301
-1.000 0.1928 0.00930 0.00281 -0.0397 0.5301 0.5406
-0.750 0.2190 0.00935 0.00281 -0.0393 0.5236 0.5476
-0.250 0.2709 0.00947 0.00280 -0.0385 0.5110 0.5612
0.000 0.2966 0.00951 0.00280 -0.0380 0.5048 0.5685
0.250 0.3220 0.00956 0.00279 -0.0375 0.4990 0.5748
0.500 0.3476 0.00956 0.00278 -0.0371 0.4906 0.5788
0.750 0.3725 0.00962 0.00277 -0.0366 0.4804 0.5814
1.000 0.3974 0.00969 0.00276 -0.0360 0.4685 0.5837
1.250 0.4229 0.00975 0.00277 -0.0356 0.4578 0.5856
1.500 0.4477 0.00981 0.00278 -0.0351 0.4482 0.5873
1.750 0.4723 0.00985 0.00280 -0.0346 0.4369 0.5889
2.000 0.4966 0.00992 0.00282 -0.0340 0.4237 0.5906
2.250 0.5205 0.01001 0.00285 -0.0334 0.4096 0.5926
2.500 0.5439 0.01012 0.00290 -0.0327 0.3944 0.5949
2.750 0.5672 0.01026 0.00297 -0.0320 0.3794 0.5976
3.000 0.5903 0.01042 0.00306 -0.0312 0.3650 0.5995
3.250 0.6126 0.01058 0.00315 -0.0304 0.3501 0.6013
3.500 0.6347 0.01074 0.00326 -0.0295 0.3365 0.6033
3.750 0.6570 0.01089 0.00338 -0.0287 0.3248 0.6055
4.000 0.6800 0.01103 0.00349 -0.0280 0.3159 0.6077
4.250 0.7022 0.01118 0.00362 -0.0272 0.3075 0.6106
4.750 0.7453 0.01146 0.00390 -0.0254 0.2903 0.6197
5.000 0.7675 0.01156 0.00403 -0.0246 0.2827 0.6253
5.250 0.7880 0.01168 0.00422 -0.0235 0.2759 0.6379
5.500 0.8059 0.01205 0.00480 -0.0216 0.2698 0.6644
6.000 0.8483 0.01240 0.00508 -0.0198 0.2565 0.7379
6.250 0.8695 0.01259 0.00527 -0.0189 0.2495 0.7410
6.500 0.8892 0.01283 0.00546 -0.0178 0.2422 0.7437
6.750 0.9098 0.01305 0.00568 -0.0169 0.2346 0.7454
7.000 0.9283 0.01335 0.00597 -0.0156 0.2258 0.7468
7.250 0.9481 0.01361 0.00623 -0.0145 0.2180 0.7484
7.500 0.9661 0.01394 0.00653 -0.0132 0.2098 0.7499
7.750 0.9849 0.01424 0.00683 -0.0121 0.2005 0.7514
8.000 1.0023 0.01460 0.00717 -0.0107 0.1915 0.7531
8.250 1.0182 0.01501 0.00754 -0.0091 0.1801 0.7545
9.000 1.0600 0.01651 0.00889 -0.0038 0.1435 0.7574
9.250 1.0730 0.01705 0.00942 -0.0020 0.1359 0.7581
9.500 1.0870 0.01755 0.00993 -0.0004 0.1301 0.7587
9.750 1.1001 0.01810 0.01048 0.0012 0.1256 0.7594
10.000 1.1135 0.01864 0.01104 0.0028 0.1207 0.7601
10.250 1.1271 0.01919 0.01162 0.0042 0.1168 0.7609
10.500 1.1384 0.01985 0.01230 0.0059 0.1120 0.7616
10.750 1.1490 0.02057 0.01303 0.0076 0.1072 0.7624
11.000 1.1632 0.02112 0.01363 0.0087 0.1028 0.7631
11.250 1.1739 0.02187 0.01440 0.0102 0.0976 0.7638
11.500 1.1834 0.02272 0.01525 0.0117 0.0910 0.7646
11.750 1.1782 0.02444 0.01676 0.0147 0.0627 0.7654
12.000 1.1706 0.02644 0.01866 0.0175 0.0452 0.7658
12.250 1.1500 0.02952 0.02163 0.0210 0.0178 0.7663
12.500 1.1506 0.03135 0.02352 0.0223 0.0143 0.7667
12.750 1.1563 0.03287 0.02512 0.0231 0.0133 0.7671
13.000 1.1602 0.03462 0.02695 0.0238 0.0122 0.7675
13.250 1.1620 0.03661 0.02904 0.0245 0.0114 0.7679
13.500 1.1628 0.03880 0.03132 0.0250 0.0107 0.7683
13.750 1.1664 0.04079 0.03339 0.0252 0.0102 0.7686
14.000 1.1689 0.04296 0.03565 0.0254 0.0096 0.7689
14.250 1.1704 0.04527 0.03806 0.0254 0.0092 0.7692
14.500 1.1698 0.04787 0.04076 0.0253 0.0087 0.7695
14.750 1.1688 0.05059 0.04358 0.0251 0.0083 0.7698
15.000 1.1656 0.05365 0.04675 0.0249 0.0082 0.7701
15.250 1.1589 0.05720 0.05041 0.0244 0.0078 0.7703
15.500 1.1568 0.06032 0.05363 0.0238 0.0077 0.7705
15.750 1.1539 0.06362 0.05704 0.0230 0.0073 0.7710
16.000 1.1490 0.06726 0.06079 0.0221 0.0074 0.7712
16.250 1.1426 0.07126 0.06490 0.0210 0.0071 0.7714
16.500 1.1367 0.07528 0.06903 0.0198 0.0068 0.7718
16.750 1.1293 0.07964 0.07350 0.0184 0.0069 0.7720
17.000 1.1233 0.08389 0.07785 0.0169 0.0065 0.7722
17.250 1.1124 0.08899 0.08308 0.0150 0.0066 0.7725
17.500 1.1051 0.09366 0.08784 0.0132 0.0063 0.7727
17.750 1.0909 0.09954 0.09386 0.0110 0.0064 0.7728
18.000 1.0799 0.10500 0.09943 0.0088 0.0063 0.7730
18.250 1.0711 0.11014 0.10466 0.0066 0.0061 0.7732
18.500 1.0586 0.11604 0.11067 0.0041 0.0061 0.7733
18.750 1.0456 0.12208 0.11682 0.0015 0.0061 0.7734
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