Eiffel 385 (S.T. Ae) (eiffel385-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 385 (S.T. Ae) (eiffel385-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.94 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel385-il-1000000-n5.txt Download as CSV file: xf-eiffel385-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 385 (S.T. Ae)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.8229 0.08379 0.08083 -0.0732 1.0000 0.0247
-18.750 -0.8353 0.07892 0.07591 -0.0759 1.0000 0.0249
-18.500 -0.8459 0.07449 0.07145 -0.0782 1.0000 0.0251
-18.250 -0.8633 0.06929 0.06620 -0.0812 1.0000 0.0252
-18.000 -0.8846 0.06400 0.06086 -0.0842 1.0000 0.0253
-17.750 -0.9230 0.05718 0.05397 -0.0882 1.0000 0.0253
-17.250 -1.0610 0.02593 0.02200 -0.1218 0.9893 0.0248
-17.000 -1.0381 0.02411 0.02008 -0.1236 0.9861 0.0252
-16.750 -1.0124 0.02276 0.01865 -0.1250 0.9839 0.0256
-16.500 -0.9852 0.02160 0.01739 -0.1262 0.9822 0.0259
-16.250 -0.9639 0.02071 0.01643 -0.1257 0.9774 0.0262
-16.000 -0.9375 0.01985 0.01549 -0.1261 0.9738 0.0266
-15.500 -0.8818 0.01833 0.01382 -0.1270 0.9676 0.0273
-15.250 -0.8556 0.01767 0.01309 -0.1270 0.9624 0.0275
-15.000 -0.8237 0.01708 0.01243 -0.1279 0.9592 0.0277
-14.750 -0.7908 0.01619 0.01146 -0.1294 0.9562 0.0284
-14.500 -0.7624 0.01552 0.01073 -0.1298 0.9491 0.0288
-14.250 -0.7297 0.01490 0.01005 -0.1308 0.9436 0.0293
-14.000 -0.6988 0.01437 0.00946 -0.1314 0.9368 0.0298
-13.750 -0.6687 0.01390 0.00892 -0.1318 0.9291 0.0303
-13.500 -0.6397 0.01349 0.00844 -0.1319 0.9216 0.0308
-13.250 -0.6121 0.01312 0.00800 -0.1316 0.9129 0.0313
-13.000 -0.5850 0.01278 0.00758 -0.1312 0.9046 0.0317
-12.750 -0.5587 0.01247 0.00719 -0.1307 0.8949 0.0320
-12.500 -0.5330 0.01214 0.00679 -0.1300 0.8857 0.0326
-12.250 -0.5077 0.01180 0.00638 -0.1292 0.8756 0.0333
-12.000 -0.4823 0.01149 0.00602 -0.1284 0.8665 0.0341
-11.750 -0.4569 0.01123 0.00568 -0.1276 0.8560 0.0350
-11.500 -0.4313 0.01098 0.00537 -0.1268 0.8446 0.0359
-11.250 -0.4058 0.01077 0.00509 -0.1260 0.8322 0.0368
-11.000 -0.3807 0.01054 0.00478 -0.1251 0.8181 0.0384
-10.500 -0.3310 0.01012 0.00422 -0.1232 0.7847 0.0432
-10.250 -0.3067 0.00990 0.00393 -0.1221 0.7636 0.0477
-10.000 -0.2829 0.00969 0.00365 -0.1210 0.7396 0.0550
-9.750 -0.2593 0.00946 0.00339 -0.1199 0.7166 0.0667
-9.500 -0.2346 0.00933 0.00322 -0.1189 0.6955 0.0770
-9.250 -0.2091 0.00926 0.00309 -0.1181 0.6779 0.0828
-8.750 -0.1563 0.00914 0.00286 -0.1167 0.6528 0.0904
-8.500 -0.1296 0.00910 0.00276 -0.1161 0.6433 0.0924
-8.250 -0.1027 0.00900 0.00264 -0.1155 0.6354 0.0956
-8.000 -0.0760 0.00893 0.00253 -0.1149 0.6281 0.0982
-7.750 -0.0486 0.00886 0.00244 -0.1145 0.6225 0.1005
-7.500 -0.0212 0.00882 0.00235 -0.1140 0.6164 0.1025
-7.250 0.0060 0.00880 0.00228 -0.1135 0.6107 0.1036
-7.000 0.0333 0.00870 0.00217 -0.1130 0.6059 0.1069
-6.750 0.0607 0.00861 0.00208 -0.1126 0.6010 0.1095
-6.500 0.0877 0.00855 0.00199 -0.1121 0.5948 0.1121
-6.250 0.1148 0.00851 0.00192 -0.1116 0.5880 0.1147
-6.000 0.1422 0.00847 0.00185 -0.1112 0.5809 0.1165
-5.750 0.1692 0.00841 0.00178 -0.1107 0.5752 0.1213
-5.500 0.1964 0.00833 0.00172 -0.1103 0.5708 0.1272
-5.250 0.2239 0.00825 0.00166 -0.1100 0.5664 0.1356
-5.000 0.2510 0.00816 0.00163 -0.1096 0.5616 0.1521
-4.750 0.2782 0.00814 0.00164 -0.1092 0.5566 0.1665
-4.500 0.3058 0.00813 0.00163 -0.1089 0.5522 0.1728
-4.250 0.3335 0.00811 0.00163 -0.1086 0.5474 0.1785
-4.000 0.3611 0.00812 0.00163 -0.1082 0.5422 0.1824
-3.750 0.3882 0.00816 0.00163 -0.1078 0.5365 0.1847
-3.500 0.4160 0.00815 0.00162 -0.1076 0.5314 0.1875
-3.250 0.4434 0.00815 0.00163 -0.1073 0.5256 0.1907
-3.000 0.4702 0.00818 0.00164 -0.1069 0.5194 0.1941
-2.750 0.4978 0.00819 0.00166 -0.1066 0.5129 0.1967
-2.500 0.5247 0.00823 0.00167 -0.1062 0.5054 0.1983
-2.250 0.5518 0.00826 0.00169 -0.1059 0.4986 0.1995
-2.000 0.5787 0.00831 0.00171 -0.1055 0.4898 0.2005
-1.750 0.6052 0.00836 0.00173 -0.1051 0.4810 0.2018
-1.500 0.6316 0.00841 0.00176 -0.1047 0.4715 0.2042
-1.250 0.6580 0.00845 0.00180 -0.1043 0.4630 0.2070
-0.750 0.7099 0.00862 0.00191 -0.1034 0.4404 0.2108
-0.500 0.7348 0.00876 0.00199 -0.1027 0.4228 0.2126
-0.250 0.7592 0.00893 0.00209 -0.1020 0.4042 0.2145
0.000 0.7844 0.00907 0.00218 -0.1014 0.3903 0.2164
0.500 0.8341 0.00934 0.00239 -0.1003 0.3660 0.2219
0.750 0.8585 0.00950 0.00251 -0.0996 0.3524 0.2257
1.000 0.8828 0.00965 0.00263 -0.0989 0.3393 0.2303
1.250 0.9072 0.00980 0.00276 -0.0983 0.3279 0.2351
1.500 0.9305 0.00999 0.00291 -0.0975 0.3138 0.2417
1.750 0.9539 0.01018 0.00307 -0.0967 0.3015 0.2505
2.000 0.9779 0.01029 0.00322 -0.0960 0.2920 0.2678
2.250 1.0007 0.01041 0.00340 -0.0952 0.2828 0.3097
2.500 1.0239 0.01055 0.00359 -0.0944 0.2724 0.3411
2.750 1.0466 0.01074 0.00378 -0.0936 0.2616 0.3582
3.000 1.0687 0.01095 0.00397 -0.0926 0.2510 0.3718
3.250 1.0911 0.01114 0.00416 -0.0917 0.2405 0.3844
3.500 1.1123 0.01137 0.00438 -0.0906 0.2287 0.3949
3.750 1.1321 0.01166 0.00462 -0.0893 0.2139 0.4044
4.000 1.1481 0.01204 0.00492 -0.0873 0.1922 0.4156
4.250 1.1610 0.01245 0.00525 -0.0847 0.1694 0.4335
4.500 1.1683 0.01307 0.00576 -0.0811 0.1355 0.4663
4.750 1.1642 0.01291 0.00637 -0.0752 0.1121 0.8604
5.250 1.2452 0.01461 0.00791 -0.0831 0.0594 1.0000
5.500 1.2623 0.01502 0.00830 -0.0815 0.0560 1.0000
5.750 1.2800 0.01541 0.00869 -0.0801 0.0534 1.0000
6.000 1.2982 0.01579 0.00908 -0.0788 0.0522 1.0000
6.250 1.3163 0.01618 0.00949 -0.0775 0.0511 1.0000
6.500 1.3332 0.01664 0.00996 -0.0761 0.0496 1.0000
6.750 1.3498 0.01713 0.01046 -0.0747 0.0484 1.0000
7.000 1.3658 0.01767 0.01101 -0.0733 0.0472 1.0000
7.250 1.3814 0.01824 0.01160 -0.0720 0.0461 1.0000
7.500 1.3985 0.01874 0.01213 -0.0709 0.0456 1.0000
7.750 1.4150 0.01928 0.01271 -0.0697 0.0448 1.0000
8.000 1.4310 0.01987 0.01332 -0.0686 0.0437 1.0000
8.250 1.4456 0.02056 0.01403 -0.0674 0.0425 1.0000
8.500 1.4592 0.02132 0.01481 -0.0662 0.0413 1.0000
8.750 1.4719 0.02218 0.01569 -0.0649 0.0401 1.0000
9.000 1.4841 0.02309 0.01663 -0.0636 0.0394 1.0000
9.250 1.4985 0.02388 0.01747 -0.0627 0.0389 1.0000
9.500 1.5118 0.02477 0.01840 -0.0617 0.0384 1.0000
9.750 1.5244 0.02573 0.01941 -0.0608 0.0378 1.0000
10.000 1.5361 0.02679 0.02050 -0.0599 0.0370 1.0000
10.250 1.5469 0.02795 0.02170 -0.0590 0.0361 1.0000
10.500 1.5568 0.02923 0.02301 -0.0581 0.0353 1.0000
10.750 1.5654 0.03065 0.02447 -0.0573 0.0345 1.0000
11.000 1.5731 0.03218 0.02604 -0.0565 0.0337 1.0000
11.250 1.5829 0.03359 0.02751 -0.0559 0.0331 1.0000
11.500 1.5915 0.03515 0.02912 -0.0554 0.0324 1.0000
11.750 1.5990 0.03683 0.03086 -0.0549 0.0316 1.0000
12.000 1.6055 0.03867 0.03274 -0.0545 0.0307 1.0000
12.250 1.6108 0.04067 0.03479 -0.0541 0.0299 1.0000
12.500 1.6149 0.04285 0.03701 -0.0538 0.0291 1.0000
12.750 1.6194 0.04501 0.03924 -0.0536 0.0285 1.0000
13.000 1.6235 0.04725 0.04154 -0.0534 0.0275 1.0000
13.250 1.6262 0.04967 0.04403 -0.0533 0.0269 1.0000
13.500 1.6282 0.05221 0.04662 -0.0533 0.0258 1.0000
13.750 1.6281 0.05499 0.04943 -0.0532 0.0245 1.0000
14.000 1.6284 0.05776 0.05227 -0.0533 0.0238 1.0000
14.250 1.6272 0.06077 0.05534 -0.0534 0.0225 1.0000
14.500 1.6250 0.06395 0.05858 -0.0536 0.0218 1.0000
14.750 1.6213 0.06734 0.06202 -0.0539 0.0208 1.0000
15.000 1.6180 0.07073 0.06548 -0.0542 0.0198 1.0000
15.250 1.6128 0.07441 0.06922 -0.0547 0.0188 1.0000
15.500 1.6068 0.07828 0.07316 -0.0552 0.0181 1.0000
15.750 1.6005 0.08223 0.07718 -0.0559 0.0175 1.0000
16.000 1.5933 0.08634 0.08137 -0.0566 0.0167 1.0000
16.250 1.5861 0.09050 0.08561 -0.0575 0.0162 1.0000
16.500 1.5783 0.09482 0.09000 -0.0585 0.0157 1.0000
16.750 1.5692 0.09930 0.09456 -0.0595 0.0151 1.0000
17.000 1.5605 0.10378 0.09911 -0.0606 0.0147 1.0000
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