Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 371 (Monge) (eiffel371-il) Reynolds number: 500,000 Max Cl/Cd: 70.14 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel371-il-500000.txt Download as CSV file: xf-eiffel371-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3180 0.08748 0.08548 -0.0423 1.0000 0.0259
-10.500 -0.3255 0.08412 0.08215 -0.0419 1.0000 0.0261
-10.250 -0.3348 0.08065 0.07871 -0.0416 1.0000 0.0263
-10.000 -0.3442 0.07469 0.07277 -0.0443 0.9994 0.0265
-9.750 -0.3485 0.06781 0.06589 -0.0492 0.9978 0.0270
-9.500 -0.5539 0.05612 0.05344 -0.0609 0.9916 0.0253
-9.250 -0.5432 0.05200 0.04927 -0.0626 0.9872 0.0256
-9.000 -0.5255 0.04919 0.04640 -0.0644 0.9841 0.0260
-8.750 -0.5545 0.03709 0.03347 -0.0619 0.9745 0.0195
-8.500 -0.5432 0.03205 0.02796 -0.0618 0.9708 0.0191
-8.250 -0.5349 0.02820 0.02366 -0.0596 0.9641 0.0187
-8.000 -0.5152 0.02472 0.01970 -0.0588 0.9600 0.0184
-7.750 -0.4860 0.02228 0.01692 -0.0594 0.9577 0.0186
-7.500 -0.4519 0.02057 0.01495 -0.0607 0.9561 0.0192
-7.250 -0.4255 0.01925 0.01342 -0.0602 0.9507 0.0196
-7.000 -0.3930 0.01817 0.01218 -0.0609 0.9464 0.0200
-6.750 -0.3581 0.01661 0.01050 -0.0623 0.9432 0.0207
-6.500 -0.3216 0.01562 0.00953 -0.0641 0.9402 0.0219
-6.250 -0.2971 0.01511 0.00900 -0.0632 0.9312 0.0230
-6.000 -0.2625 0.01436 0.00818 -0.0643 0.9256 0.0241
-5.750 -0.2360 0.01393 0.00766 -0.0637 0.9153 0.0250
-5.500 -0.2095 0.01288 0.00660 -0.0634 0.9055 0.0266
-5.250 -0.1834 0.01240 0.00609 -0.0628 0.8932 0.0282
-5.000 -0.1589 0.01207 0.00570 -0.0619 0.8787 0.0302
-4.750 -0.1370 0.01153 0.00511 -0.0604 0.8621 0.0329
-4.500 -0.1134 0.01120 0.00471 -0.0593 0.8425 0.0359
-4.250 -0.0920 0.01085 0.00427 -0.0576 0.8164 0.0403
-4.000 -0.0702 0.01062 0.00392 -0.0561 0.7849 0.0476
-3.750 -0.0505 0.01039 0.00365 -0.0541 0.7518 0.0676
-3.500 -0.0321 0.01015 0.00343 -0.0521 0.7226 0.1056
-3.000 0.0016 0.00947 0.00308 -0.0477 0.6799 0.2422
-2.750 0.0118 0.00886 0.00298 -0.0443 0.6650 0.3999
-2.500 0.0279 0.00863 0.00304 -0.0418 0.6518 0.4854
-2.250 0.0531 0.00879 0.00312 -0.0410 0.6395 0.5285
-2.000 0.0781 0.00894 0.00316 -0.0402 0.6291 0.5471
-1.750 0.1024 0.00906 0.00317 -0.0393 0.6191 0.5622
-1.500 0.1266 0.00910 0.00314 -0.0384 0.6102 0.5758
-1.250 0.1510 0.00910 0.00306 -0.0376 0.6017 0.5860
-1.000 0.1765 0.00904 0.00297 -0.0371 0.5938 0.5921
-0.750 0.2014 0.00902 0.00288 -0.0364 0.5859 0.5993
-0.500 0.2261 0.00890 0.00277 -0.0358 0.5789 0.6075
-0.250 0.2499 0.00879 0.00265 -0.0350 0.5716 0.6181
0.000 0.2716 0.00860 0.00253 -0.0337 0.5649 0.6312
0.250 0.2876 0.00853 0.00279 -0.0311 0.5582 0.6577
0.500 0.3107 0.00942 0.00390 -0.0289 0.5518 0.6878
0.750 0.3394 0.00899 0.00320 -0.0300 0.5444 0.7486
1.000 0.3653 0.00914 0.00325 -0.0296 0.5360 0.7531
1.250 0.3910 0.00924 0.00332 -0.0292 0.5264 0.7569
1.500 0.4164 0.00940 0.00339 -0.0288 0.5179 0.7605
1.750 0.4426 0.00949 0.00345 -0.0285 0.5101 0.7634
2.000 0.4681 0.00964 0.00351 -0.0281 0.5024 0.7655
2.250 0.4940 0.00972 0.00361 -0.0278 0.4937 0.7672
2.500 0.5189 0.00987 0.00370 -0.0272 0.4850 0.7690
2.750 0.5442 0.00997 0.00381 -0.0268 0.4749 0.7714
3.000 0.5689 0.01010 0.00391 -0.0263 0.4646 0.7738
3.250 0.5928 0.01026 0.00400 -0.0256 0.4530 0.7761
3.500 0.6172 0.01039 0.00411 -0.0251 0.4404 0.7780
3.750 0.6410 0.01056 0.00421 -0.0245 0.4264 0.7794
4.000 0.6638 0.01069 0.00430 -0.0237 0.4103 0.7808
4.250 0.6859 0.01087 0.00444 -0.0228 0.3936 0.7826
4.500 0.7077 0.01109 0.00459 -0.0218 0.3779 0.7846
4.750 0.7296 0.01131 0.00476 -0.0209 0.3636 0.7864
5.000 0.7514 0.01154 0.00494 -0.0200 0.3515 0.7882
5.250 0.7730 0.01177 0.00513 -0.0191 0.3407 0.7893
5.500 0.7945 0.01201 0.00531 -0.0182 0.3303 0.7902
5.750 0.8166 0.01221 0.00550 -0.0175 0.3212 0.7910
6.000 0.8363 0.01248 0.00571 -0.0162 0.3121 0.7918
6.250 0.8580 0.01266 0.00590 -0.0154 0.3042 0.7925
6.750 0.8977 0.01305 0.00628 -0.0131 0.2893 0.7939
7.000 0.9160 0.01326 0.00648 -0.0117 0.2821 0.7946
7.250 0.9363 0.01342 0.00668 -0.0107 0.2750 0.7955
7.500 0.9546 0.01367 0.00691 -0.0093 0.2671 0.7962
7.750 0.9743 0.01389 0.00716 -0.0082 0.2597 0.7971
8.000 0.9916 0.01419 0.00745 -0.0067 0.2509 0.7980
8.250 1.0105 0.01444 0.00772 -0.0056 0.2410 0.7990
8.500 1.0270 0.01478 0.00804 -0.0041 0.2299 0.8000
8.750 1.0423 0.01517 0.00839 -0.0024 0.2170 0.8008
9.000 1.0566 0.01561 0.00878 -0.0006 0.2028 0.8015
9.250 1.0700 0.01609 0.00921 0.0012 0.1895 0.8021
9.500 1.0822 0.01663 0.00969 0.0032 0.1755 0.8027
9.750 1.0953 0.01714 0.01018 0.0050 0.1650 0.8033
10.000 1.1072 0.01769 0.01073 0.0069 0.1569 0.8041
10.250 1.1183 0.01830 0.01131 0.0089 0.1499 0.8047
10.500 1.1307 0.01887 0.01190 0.0106 0.1449 0.8051
10.750 1.1426 0.01947 0.01251 0.0122 0.1396 0.8054
11.000 1.1508 0.02026 0.01328 0.0143 0.1341 0.8058
11.250 1.1647 0.02081 0.01389 0.0155 0.1299 0.8061
11.500 1.1751 0.02154 0.01463 0.0171 0.1252 0.8064
11.750 1.1809 0.02252 0.01560 0.0191 0.1200 0.8066
12.000 1.1957 0.02305 0.01622 0.0200 0.1163 0.8070
12.250 1.2041 0.02394 0.01711 0.0214 0.1105 0.8074
12.500 1.2127 0.02487 0.01808 0.0227 0.1051 0.8077
12.750 1.2210 0.02587 0.01907 0.0240 0.0961 0.8080
13.000 1.2269 0.02708 0.02024 0.0252 0.0830 0.8083
13.250 1.2108 0.02986 0.02278 0.0280 0.0537 0.8085
13.500 1.2000 0.03253 0.02540 0.0299 0.0384 0.8086
13.750 1.1790 0.03626 0.02906 0.0318 0.0213 0.8087
14.000 1.1742 0.03889 0.03176 0.0326 0.0185 0.8088
14.250 1.1745 0.04117 0.03413 0.0329 0.0179 0.8091
14.500 1.1677 0.04424 0.03731 0.0332 0.0164 0.8091
14.750 1.1664 0.04687 0.04005 0.0332 0.0159 0.8093
15.000 1.1638 0.04973 0.04303 0.0331 0.0155 0.8095
15.250 1.1609 0.05272 0.04613 0.0327 0.0151 0.8097
15.500 1.1574 0.05584 0.04937 0.0323 0.0150 0.8100
15.750 1.1490 0.05967 0.05332 0.0316 0.0145 0.8102
16.000 1.1430 0.06334 0.05710 0.0307 0.0143 0.8104
16.250 1.1310 0.06793 0.06181 0.0296 0.0139 0.8105
16.500 1.1162 0.07308 0.06708 0.0282 0.0134 0.8105
16.750 1.1097 0.07728 0.07139 0.0267 0.0135 0.8106
17.000 1.0973 0.08247 0.07670 0.0250 0.0135 0.8107
17.250 1.0829 0.08811 0.08246 0.0229 0.0133 0.8108
17.500 1.0727 0.09322 0.08767 0.0209 0.0133 0.8110
17.750 1.0517 0.10019 0.09476 0.0183 0.0129 0.8110
18.000 1.0407 0.10565 0.10033 0.0161 0.0130 0.8111
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