E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E174 (Dicke 8.92%) (e174-il) Reynolds number: 50,000 Max Cl/Cd: 39.04 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e174-il-50000-n5.txt Download as CSV file: xf-e174-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3446 0.10405 0.09738 -0.0280 1.0000 0.1006
-8.250 -0.3549 0.10276 0.09626 -0.0315 1.0000 0.1038
-8.000 -0.3627 0.10087 0.09451 -0.0340 1.0000 0.1043
-7.750 -0.3522 0.09634 0.09006 -0.0332 1.0000 0.1056
-7.500 -0.3389 0.09249 0.08623 -0.0317 1.0000 0.1085
-7.250 -0.3376 0.08984 0.08368 -0.0316 1.0000 0.1111
-7.000 -0.3387 0.08457 0.07847 -0.0358 1.0000 0.0716
-6.500 -0.3453 0.07540 0.06943 -0.0448 1.0000 0.0501
-6.250 -0.3473 0.07286 0.06698 -0.0435 1.0000 0.0496
-6.000 -0.3515 0.07055 0.06474 -0.0422 1.0000 0.0491
-5.750 -0.3448 0.06717 0.06135 -0.0439 0.9960 0.0484
-5.500 -0.3134 0.06159 0.05560 -0.0515 0.9840 0.0469
-5.250 -0.2802 0.05577 0.04953 -0.0591 0.9723 0.0452
-5.000 -0.2465 0.05001 0.04336 -0.0659 0.9605 0.0436
-4.750 -0.2115 0.04458 0.03742 -0.0717 0.9496 0.0424
-4.500 -0.1740 0.03982 0.03204 -0.0766 0.9407 0.0417
-4.250 -0.1370 0.03591 0.02749 -0.0801 0.9316 0.0419
-4.000 -0.1019 0.03294 0.02394 -0.0824 0.9222 0.0430
-3.750 -0.0634 0.03045 0.02085 -0.0848 0.9148 0.0471
-3.500 -0.0302 0.02848 0.01820 -0.0856 0.9047 0.0505
-3.250 0.0034 0.02663 0.01619 -0.0867 0.8965 0.0542
-3.000 0.0364 0.02524 0.01449 -0.0873 0.8877 0.0612
-2.750 0.0673 0.02416 0.01320 -0.0876 0.8783 0.0757
-2.500 0.1014 0.02296 0.01204 -0.0888 0.8708 0.1116
-2.250 0.1295 0.02179 0.01118 -0.0892 0.8609 0.1927
-2.000 0.1578 0.02048 0.01065 -0.0896 0.8527 0.3644
-1.750 0.1757 0.01927 0.01055 -0.0868 0.8439 0.6420
-1.500 0.2209 0.01853 0.00992 -0.0885 0.8367 1.0000
-1.250 0.2504 0.01868 0.00961 -0.0888 0.8281 1.0000
-1.000 0.2765 0.01892 0.00948 -0.0886 0.8185 1.0000
-0.750 0.3062 0.01908 0.00928 -0.0888 0.8111 1.0000
-0.500 0.3313 0.01936 0.00930 -0.0885 0.8015 1.0000
-0.250 0.3585 0.01961 0.00929 -0.0884 0.7935 1.0000
0.000 0.3856 0.01987 0.00933 -0.0883 0.7854 1.0000
0.250 0.4116 0.02018 0.00945 -0.0882 0.7770 1.0000
0.500 0.4394 0.02044 0.00953 -0.0881 0.7699 1.0000
0.750 0.4644 0.02081 0.00978 -0.0878 0.7613 1.0000
1.000 0.4923 0.02107 0.00990 -0.0877 0.7546 1.0000
1.250 0.5165 0.02150 0.01025 -0.0874 0.7461 1.0000
1.500 0.5445 0.02176 0.01042 -0.0873 0.7397 1.0000
1.750 0.5680 0.02225 0.01087 -0.0869 0.7310 1.0000
2.000 0.5960 0.02252 0.01109 -0.0868 0.7249 1.0000
2.250 0.6189 0.02306 0.01164 -0.0863 0.7161 1.0000
2.500 0.6469 0.02333 0.01187 -0.0861 0.7101 1.0000
2.750 0.6691 0.02393 0.01251 -0.0856 0.7011 1.0000
3.000 0.6974 0.02419 0.01280 -0.0854 0.6952 1.0000
3.250 0.7188 0.02484 0.01352 -0.0849 0.6858 1.0000
3.500 0.7466 0.02512 0.01383 -0.0846 0.6796 1.0000
3.750 0.7682 0.02577 0.01458 -0.0840 0.6701 1.0000
4.000 0.7930 0.02622 0.01515 -0.0835 0.6622 1.0000
4.250 0.8178 0.02663 0.01567 -0.0829 0.6538 1.0000
4.500 0.8400 0.02721 0.01638 -0.0822 0.6439 1.0000
4.750 0.8690 0.02730 0.01656 -0.0817 0.6367 1.0000
5.000 0.8897 0.02791 0.01738 -0.0808 0.6251 1.0000
5.250 0.9120 0.02837 0.01801 -0.0798 0.6139 1.0000
5.500 0.9364 0.02863 0.01844 -0.0789 0.6028 1.0000
5.750 0.9629 0.02865 0.01862 -0.0779 0.5916 1.0000
6.000 0.9883 0.02868 0.01889 -0.0768 0.5790 1.0000
6.250 1.0118 0.02876 0.01918 -0.0755 0.5646 1.0000
6.500 1.0325 0.02897 0.01962 -0.0740 0.5479 1.0000
6.750 1.0530 0.02909 0.01999 -0.0723 0.5295 1.0000
7.000 1.0760 0.02889 0.02005 -0.0706 0.5098 1.0000
7.250 1.0949 0.02894 0.02034 -0.0686 0.4863 1.0000
7.500 1.1135 0.02893 0.02054 -0.0665 0.4590 1.0000
7.750 1.1302 0.02900 0.02079 -0.0641 0.4253 1.0000
8.000 1.1436 0.02929 0.02112 -0.0615 0.3817 1.0000
8.250 1.1523 0.03000 0.02170 -0.0585 0.3255 1.0000
8.500 1.1535 0.03152 0.02281 -0.0553 0.2652 1.0000
8.750 1.1471 0.03373 0.02458 -0.0520 0.2132 1.0000
9.000 1.1380 0.03634 0.02682 -0.0492 0.1702 1.0000
9.250 1.1296 0.03927 0.02943 -0.0472 0.1322 1.0000
9.500 1.1231 0.04234 0.03227 -0.0458 0.1046 1.0000
9.750 1.1194 0.04542 0.03527 -0.0446 0.0847 1.0000
10.000 1.1163 0.04858 0.03838 -0.0436 0.0720 1.0000
10.250 1.1149 0.05169 0.04148 -0.0426 0.0627 1.0000
10.500 1.1139 0.05481 0.04457 -0.0419 0.0560 1.0000
10.750 1.1195 0.05735 0.04730 -0.0409 0.0503 1.0000
11.000 1.1229 0.06013 0.05011 -0.0402 0.0464 1.0000
11.250 1.1332 0.06241 0.05262 -0.0388 0.0436 1.0000
11.500 1.1496 0.06444 0.05495 -0.0370 0.0409 1.0000
11.750 1.1656 0.06672 0.05750 -0.0356 0.0389 1.0000
12.000 1.1771 0.06953 0.06054 -0.0346 0.0375 1.0000
12.250 1.1846 0.07268 0.06386 -0.0340 0.0361 1.0000
12.500 1.1888 0.07646 0.06781 -0.0337 0.0351 1.0000
12.750 1.1828 0.08101 0.07273 -0.0343 0.0345 1.0000
13.000 1.1729 0.08613 0.07821 -0.0355 0.0341 1.0000
13.250 1.1610 0.09168 0.08405 -0.0373 0.0339 1.0000
13.500 1.1467 0.09775 0.09040 -0.0397 0.0338 1.0000
13.750 1.1308 0.10439 0.09728 -0.0428 0.0338 1.0000
14.000 1.1134 0.11165 0.10475 -0.0466 0.0339 1.0000
14.250 1.0955 0.11962 0.11289 -0.0512 0.0342 1.0000
14.500 1.0791 0.12799 0.12141 -0.0562 0.0345 1.0000
14.750 1.0638 0.13681 0.13033 -0.0616 0.0348 1.0000
15.000 1.0505 0.14589 0.13948 -0.0672 0.0351 1.0000
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Polar data table (+)
Polar graphs
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