E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: E174 (Dicke 8.92%) (e174-il) Reynolds number: 100,000 Max Cl/Cd: 61.39 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e174-il-100000.txt Download as CSV file: xf-e174-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3385 0.09758 0.09291 -0.0306 1.0000 0.0787
-8.000 -0.3479 0.09620 0.09167 -0.0343 1.0000 0.0799
-7.750 -0.3606 0.09473 0.09035 -0.0398 1.0000 0.0805
-7.500 -0.3311 0.08834 0.08390 -0.0324 1.0000 0.0847
-7.250 -0.3298 0.08590 0.08155 -0.0320 1.0000 0.0888
-7.000 -0.3357 0.08378 0.07955 -0.0327 1.0000 0.0912
-6.750 -0.3495 0.08221 0.07815 -0.0374 1.0000 0.0936
-6.500 -0.3693 0.08134 0.07739 -0.0383 1.0000 0.0941
-6.250 -0.3894 0.08070 0.07679 -0.0377 1.0000 0.0944
-6.000 -0.3906 0.07700 0.07322 -0.0341 0.9986 0.0958
-5.750 -0.3646 0.07330 0.06954 -0.0332 0.9930 0.1008
-5.500 -0.3227 0.06653 0.06257 -0.0488 0.9822 0.1108
-5.250 -0.2803 0.06115 0.05694 -0.0609 0.9725 0.1239
-5.000 -0.2556 0.05768 0.05357 -0.0604 0.9644 0.1291
-4.750 -0.2140 0.05289 0.04862 -0.0685 0.9577 0.1434
-4.500 -0.1808 0.04905 0.04463 -0.0736 0.9475 0.1586
-4.000 -0.0750 0.03192 0.02523 -0.0901 0.9329 0.0656
-3.750 -0.0325 0.02818 0.02099 -0.0935 0.9278 0.0630
-3.500 0.0017 0.02583 0.01809 -0.0946 0.9183 0.0640
-3.250 0.0412 0.02346 0.01523 -0.0963 0.9118 0.0638
-3.000 0.0757 0.02179 0.01317 -0.0969 0.9031 0.0660
-2.750 0.1084 0.02020 0.01153 -0.0975 0.8952 0.0726
-2.500 0.1409 0.01903 0.01035 -0.0979 0.8872 0.0919
-2.250 0.1675 0.01762 0.00932 -0.0975 0.8780 0.1671
-2.000 0.1932 0.01565 0.00885 -0.0973 0.8712 0.4755
-1.750 0.2363 0.01419 0.00849 -0.0979 0.8645 1.0000
-1.500 0.2660 0.01427 0.00818 -0.0980 0.8566 1.0000
-1.250 0.2905 0.01452 0.00814 -0.0975 0.8465 1.0000
-1.000 0.3179 0.01468 0.00804 -0.0972 0.8386 1.0000
-0.750 0.3437 0.01490 0.00802 -0.0968 0.8297 1.0000
-0.500 0.3692 0.01516 0.00809 -0.0964 0.8212 1.0000
-0.250 0.3963 0.01534 0.00808 -0.0961 0.8138 1.0000
0.000 0.4210 0.01568 0.00829 -0.0957 0.8050 1.0000
0.250 0.4485 0.01585 0.00829 -0.0953 0.7985 1.0000
0.500 0.4727 0.01624 0.00859 -0.0949 0.7895 1.0000
0.750 0.5004 0.01641 0.00863 -0.0946 0.7835 1.0000
1.000 0.5243 0.01685 0.00903 -0.0942 0.7744 1.0000
1.250 0.5521 0.01702 0.00909 -0.0938 0.7687 1.0000
1.500 0.5757 0.01752 0.00957 -0.0935 0.7596 1.0000
1.750 0.6036 0.01769 0.00966 -0.0931 0.7540 1.0000
2.000 0.6269 0.01823 0.01022 -0.0928 0.7448 1.0000
2.250 0.6549 0.01840 0.01033 -0.0923 0.7393 1.0000
2.500 0.6779 0.01897 0.01094 -0.0920 0.7299 1.0000
2.750 0.7051 0.01920 0.01114 -0.0916 0.7238 1.0000
3.000 0.7288 0.01970 0.01172 -0.0912 0.7148 1.0000
3.250 0.7546 0.02004 0.01207 -0.0907 0.7075 1.0000
3.500 0.7800 0.02037 0.01244 -0.0902 0.6991 1.0000
3.750 0.8042 0.02080 0.01293 -0.0896 0.6902 1.0000
4.000 0.8319 0.02086 0.01304 -0.0889 0.6828 1.0000
4.250 0.8552 0.02130 0.01358 -0.0882 0.6722 1.0000
4.500 0.8810 0.02148 0.01382 -0.0875 0.6630 1.0000
4.750 0.9085 0.02144 0.01383 -0.0867 0.6539 1.0000
5.000 0.9324 0.02169 0.01422 -0.0858 0.6422 1.0000
5.250 0.9576 0.02178 0.01442 -0.0848 0.6308 1.0000
5.500 0.9840 0.02169 0.01441 -0.0838 0.6192 1.0000
5.750 1.0112 0.02146 0.01426 -0.0828 0.6072 1.0000
6.000 1.0376 0.02123 0.01415 -0.0816 0.5934 1.0000
6.250 1.0625 0.02105 0.01410 -0.0804 0.5777 1.0000
6.500 1.0871 0.02080 0.01401 -0.0790 0.5602 1.0000
6.750 1.1126 0.02037 0.01371 -0.0776 0.5410 1.0000
7.000 1.1359 0.01991 0.01337 -0.0759 0.5161 1.0000
7.250 1.1572 0.01927 0.01276 -0.0736 0.4798 1.0000
7.500 1.1737 0.01912 0.01257 -0.0711 0.4250 1.0000
7.750 1.1845 0.01973 0.01283 -0.0682 0.3404 1.0000
8.000 1.1876 0.02145 0.01393 -0.0650 0.2445 1.0000
8.250 1.1840 0.02400 0.01578 -0.0614 0.1533 1.0000
8.500 1.1721 0.02730 0.01839 -0.0568 0.0886 1.0000
8.750 1.1681 0.02968 0.02057 -0.0530 0.0705 1.0000
9.000 1.1700 0.03169 0.02258 -0.0498 0.0618 1.0000
9.250 1.1749 0.03387 0.02465 -0.0473 0.0564 1.0000
9.500 1.1881 0.03555 0.02647 -0.0455 0.0511 1.0000
9.750 1.2069 0.03781 0.02861 -0.0445 0.0469 1.0000
10.000 1.2444 0.04075 0.03169 -0.0450 0.0447 1.0000
10.250 1.2756 0.04385 0.03514 -0.0452 0.0434 1.0000
10.500 1.2974 0.04724 0.03889 -0.0444 0.0429 1.0000
10.750 1.3109 0.05086 0.04292 -0.0430 0.0428 1.0000
11.000 1.3160 0.05438 0.04684 -0.0410 0.0426 1.0000
11.250 1.3134 0.05765 0.05048 -0.0384 0.0423 1.0000
11.500 1.3061 0.06096 0.05412 -0.0358 0.0421 1.0000
11.750 1.2951 0.06451 0.05798 -0.0336 0.0422 1.0000
12.000 1.2808 0.06835 0.06212 -0.0320 0.0422 1.0000
12.250 1.2641 0.07258 0.06663 -0.0311 0.0424 1.0000
12.500 1.2456 0.07727 0.07158 -0.0310 0.0428 1.0000
12.750 1.2255 0.08243 0.07697 -0.0317 0.0431 1.0000
13.000 1.2043 0.08813 0.08289 -0.0333 0.0435 1.0000
13.250 1.1830 0.09437 0.08931 -0.0356 0.0440 1.0000
13.500 1.1611 0.10114 0.09625 -0.0387 0.0445 1.0000
13.750 1.1412 0.10833 0.10357 -0.0422 0.0451 1.0000
14.000 1.1237 0.11590 0.11122 -0.0459 0.0456 1.0000
14.250 1.1119 0.12295 0.11840 -0.0494 0.0464 1.0000
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Polar data table (+)
Polar graphs
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