E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E174 (Dicke 8.92%) (e174-il) Reynolds number: 100,000 Max Cl/Cd: 61.41 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e174-il-100000-n5.txt Download as CSV file: xf-e174-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E174 (Dicke 8.92%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3506 0.10247 0.09767 -0.0309 1.0000 0.0498
-8.500 -0.3524 0.09992 0.09521 -0.0341 1.0000 0.0502
-8.250 -0.3535 0.09712 0.09250 -0.0365 1.0000 0.0504
-8.000 -0.3551 0.09423 0.08970 -0.0384 1.0000 0.0505
-7.750 -0.3541 0.09085 0.08640 -0.0415 1.0000 0.0506
-7.500 -0.3507 0.08638 0.08203 -0.0409 1.0000 0.0510
-7.250 -0.3466 0.08290 0.07861 -0.0396 1.0000 0.0515
-7.000 -0.3452 0.07993 0.07572 -0.0393 1.0000 0.0519
-6.750 -0.2530 0.05354 0.04950 -0.0553 0.9584 0.0287
-6.500 -0.3102 0.06457 0.06023 -0.0569 0.9777 0.0291
-6.250 -0.2882 0.06135 0.05698 -0.0590 0.9653 0.0276
-6.000 -0.2607 0.05566 0.05117 -0.0662 0.9499 0.0262
-5.750 -0.2313 0.04886 0.04411 -0.0740 0.9346 0.0246
-5.500 -0.1998 0.03905 0.03345 -0.0819 0.9194 0.0221
-5.250 -0.1725 0.03493 0.02890 -0.0846 0.9060 0.0218
-5.000 -0.1449 0.03117 0.02458 -0.0864 0.8932 0.0217
-4.750 -0.1169 0.02799 0.02081 -0.0874 0.8810 0.0218
-4.500 -0.0892 0.02549 0.01779 -0.0880 0.8696 0.0226
-4.250 -0.0627 0.02416 0.01625 -0.0882 0.8576 0.0246
-4.000 -0.0355 0.02250 0.01419 -0.0880 0.8460 0.0259
-3.750 -0.0080 0.02088 0.01219 -0.0877 0.8354 0.0268
-3.500 0.0194 0.01956 0.01054 -0.0872 0.8260 0.0279
-3.250 0.0459 0.01844 0.00924 -0.0867 0.8154 0.0294
-3.000 0.0724 0.01759 0.00831 -0.0864 0.8057 0.0326
-2.750 0.0995 0.01691 0.00747 -0.0860 0.7973 0.0398
-2.500 0.1262 0.01619 0.00666 -0.0857 0.7876 0.0521
-2.250 0.1527 0.01539 0.00607 -0.0855 0.7793 0.1064
-2.000 0.1784 0.01463 0.00580 -0.0854 0.7709 0.2265
-1.750 0.2040 0.01406 0.00559 -0.0851 0.7628 0.3568
-1.500 0.2279 0.01340 0.00546 -0.0842 0.7552 0.5399
-1.250 0.2466 0.01273 0.00543 -0.0814 0.7476 0.7597
-1.000 0.2911 0.01235 0.00506 -0.0838 0.7407 1.0000
-0.750 0.3180 0.01247 0.00493 -0.0836 0.7330 1.0000
-0.500 0.3450 0.01259 0.00481 -0.0834 0.7261 1.0000
-0.250 0.3719 0.01273 0.00477 -0.0832 0.7188 1.0000
0.000 0.3989 0.01286 0.00472 -0.0830 0.7120 1.0000
0.250 0.4258 0.01302 0.00472 -0.0829 0.7052 1.0000
0.500 0.4527 0.01317 0.00474 -0.0827 0.6984 1.0000
0.750 0.4798 0.01333 0.00478 -0.0825 0.6921 1.0000
1.000 0.5066 0.01350 0.00487 -0.0823 0.6852 1.0000
1.250 0.5338 0.01367 0.00491 -0.0821 0.6796 1.0000
1.500 0.5604 0.01387 0.00508 -0.0820 0.6723 1.0000
1.750 0.5875 0.01404 0.00517 -0.0818 0.6667 1.0000
2.000 0.6140 0.01426 0.00539 -0.0816 0.6596 1.0000
2.250 0.6410 0.01444 0.00553 -0.0814 0.6536 1.0000
2.500 0.6676 0.01466 0.00575 -0.0813 0.6470 1.0000
2.750 0.6943 0.01487 0.00598 -0.0811 0.6404 1.0000
3.000 0.7210 0.01508 0.00619 -0.0808 0.6342 1.0000
3.250 0.7473 0.01531 0.00646 -0.0806 0.6270 1.0000
3.500 0.7741 0.01551 0.00666 -0.0804 0.6207 1.0000
3.750 0.8001 0.01575 0.00700 -0.0801 0.6124 1.0000
4.000 0.8265 0.01594 0.00723 -0.0797 0.6049 1.0000
4.250 0.8524 0.01613 0.00749 -0.0793 0.5959 1.0000
4.500 0.8780 0.01633 0.00777 -0.0789 0.5861 1.0000
4.750 0.9040 0.01648 0.00801 -0.0784 0.5765 1.0000
5.000 0.9296 0.01663 0.00824 -0.0779 0.5656 1.0000
5.250 0.9546 0.01680 0.00854 -0.0773 0.5534 1.0000
5.500 0.9795 0.01696 0.00885 -0.0767 0.5404 1.0000
5.750 1.0042 0.01711 0.00911 -0.0760 0.5259 1.0000
6.000 1.0287 0.01726 0.00937 -0.0752 0.5099 1.0000
6.250 1.0526 0.01742 0.00965 -0.0744 0.4917 1.0000
6.500 1.0758 0.01764 0.01003 -0.0735 0.4696 1.0000
6.750 1.0980 0.01788 0.01036 -0.0724 0.4419 1.0000
7.000 1.1173 0.01826 0.01065 -0.0709 0.3946 1.0000
7.250 1.1315 0.01909 0.01112 -0.0689 0.3198 1.0000
7.500 1.1396 0.02064 0.01209 -0.0665 0.2354 1.0000
7.750 1.1471 0.02238 0.01336 -0.0643 0.1659 1.0000
8.000 1.1550 0.02408 0.01471 -0.0623 0.1106 1.0000
8.250 1.1645 0.02560 0.01604 -0.0603 0.0749 1.0000
8.500 1.1718 0.02727 0.01755 -0.0580 0.0485 1.0000
8.750 1.1780 0.02895 0.01919 -0.0556 0.0371 1.0000
9.000 1.1827 0.03051 0.02084 -0.0529 0.0324 1.0000
9.250 1.1876 0.03209 0.02255 -0.0505 0.0293 1.0000
9.500 1.1903 0.03391 0.02445 -0.0483 0.0272 1.0000
9.750 1.1938 0.03578 0.02645 -0.0464 0.0254 1.0000
10.000 1.1989 0.03761 0.02845 -0.0449 0.0239 1.0000
10.250 1.2034 0.03959 0.03059 -0.0435 0.0224 1.0000
10.500 1.2071 0.04176 0.03289 -0.0422 0.0216 1.0000
10.750 1.2113 0.04397 0.03522 -0.0411 0.0210 1.0000
11.000 1.2150 0.04637 0.03772 -0.0400 0.0204 1.0000
11.250 1.2199 0.04889 0.04030 -0.0389 0.0199 1.0000
11.500 1.2290 0.05117 0.04277 -0.0378 0.0195 1.0000
11.750 1.2384 0.05355 0.04536 -0.0368 0.0192 1.0000
12.000 1.2470 0.05618 0.04822 -0.0359 0.0188 1.0000
12.250 1.2535 0.05909 0.05141 -0.0351 0.0186 1.0000
12.500 1.2568 0.06234 0.05494 -0.0345 0.0183 1.0000
12.750 1.2562 0.06591 0.05879 -0.0343 0.0180 1.0000
13.000 1.2521 0.06983 0.06299 -0.0344 0.0177 1.0000
13.250 1.2457 0.07400 0.06741 -0.0349 0.0173 1.0000
13.500 1.2372 0.07860 0.07227 -0.0359 0.0171 1.0000
13.750 1.2265 0.08361 0.07753 -0.0373 0.0169 1.0000
14.000 1.2138 0.08907 0.08323 -0.0392 0.0167 1.0000
14.250 1.1985 0.09526 0.08967 -0.0419 0.0167 1.0000
14.500 1.1821 0.10197 0.09662 -0.0452 0.0167 1.0000
14.750 1.1623 0.10993 0.10482 -0.0496 0.0169 1.0000
15.000 1.1409 0.11893 0.11405 -0.0550 0.0171 1.0000
15.250 1.1168 0.12955 0.12487 -0.0619 0.0175 1.0000
15.500 1.0921 0.14158 0.13706 -0.0698 0.0181 1.0000
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Polar data table (+)
Polar graphs
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