E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E174 (Dicke 8.92%) (e174-il) Reynolds number: 500,000 Max Cl/Cd: 117.35 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e174-il-500000.txt Download as CSV file: xf-e174-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3350 0.08401 0.08190 -0.0346 1.0000 0.0168
-7.750 -0.3355 0.08084 0.07878 -0.0360 1.0000 0.0169
-7.500 -0.3395 0.07813 0.07614 -0.0362 1.0000 0.0169
-7.250 -0.3300 0.07356 0.07161 -0.0418 0.9915 0.0170
-7.000 -0.3036 0.06475 0.06277 -0.0555 0.9743 0.0172
-6.750 -0.2782 0.05988 0.05785 -0.0627 0.9553 0.0179
-6.500 -0.2514 0.05563 0.05350 -0.0692 0.9271 0.0185
-6.250 -0.2346 0.05156 0.04925 -0.0732 0.8942 0.0191
-6.000 -0.2192 0.04729 0.04478 -0.0764 0.8680 0.0198
-5.750 -0.2012 0.04250 0.03974 -0.0795 0.8468 0.0211
-5.500 -0.1742 0.03741 0.03411 -0.0822 0.8297 0.0231
-5.250 -0.1622 0.03065 0.02700 -0.0843 0.8151 0.0244
-5.000 -0.1404 0.02895 0.02515 -0.0846 0.8015 0.0254
-4.750 -0.1169 0.02698 0.02295 -0.0849 0.7893 0.0273
-4.500 -0.0866 0.02712 0.02260 -0.0842 0.7780 0.0313
-4.250 -0.0659 0.01686 0.01132 -0.0842 0.7698 0.0190
-4.000 -0.0389 0.01505 0.00913 -0.0839 0.7600 0.0188
-3.750 -0.0112 0.01369 0.00741 -0.0833 0.7512 0.0176
-3.500 0.0163 0.01304 0.00659 -0.0830 0.7422 0.0172
-3.250 0.0435 0.01215 0.00556 -0.0828 0.7340 0.0170
-3.000 0.0703 0.01116 0.00443 -0.0824 0.7263 0.0172
-2.750 0.0974 0.01029 0.00346 -0.0823 0.7185 0.0181
-2.500 0.1249 0.00989 0.00297 -0.0821 0.7114 0.0201
-2.250 0.1529 0.00960 0.00261 -0.0820 0.7042 0.0225
-2.000 0.1808 0.00927 0.00223 -0.0819 0.6975 0.0335
-1.750 0.2083 0.00872 0.00200 -0.0820 0.6908 0.1223
-1.500 0.2356 0.00840 0.00189 -0.0821 0.6843 0.2029
-1.250 0.2626 0.00795 0.00185 -0.0822 0.6783 0.3412
-1.000 0.2888 0.00741 0.00185 -0.0822 0.6719 0.5201
-0.750 0.3132 0.00693 0.00187 -0.0815 0.6664 0.7004
-0.500 0.3323 0.00643 0.00191 -0.0791 0.6604 0.8839
-0.250 0.3739 0.00633 0.00179 -0.0817 0.6545 1.0000
0.000 0.4017 0.00640 0.00177 -0.0817 0.6487 1.0000
0.250 0.4294 0.00646 0.00175 -0.0816 0.6429 1.0000
0.500 0.4571 0.00657 0.00175 -0.0816 0.6376 1.0000
0.750 0.4850 0.00662 0.00176 -0.0816 0.6316 1.0000
1.000 0.5128 0.00670 0.00178 -0.0815 0.6261 1.0000
1.250 0.5406 0.00679 0.00181 -0.0815 0.6206 1.0000
1.500 0.5684 0.00686 0.00185 -0.0815 0.6146 1.0000
2.000 0.6239 0.00703 0.00196 -0.0814 0.6031 1.0000
2.250 0.6516 0.00713 0.00200 -0.0813 0.5970 1.0000
2.500 0.6792 0.00721 0.00207 -0.0813 0.5902 1.0000
2.750 0.7068 0.00729 0.00213 -0.0812 0.5830 1.0000
3.000 0.7343 0.00737 0.00222 -0.0812 0.5755 1.0000
3.250 0.7617 0.00746 0.00229 -0.0811 0.5680 1.0000
3.500 0.7892 0.00754 0.00238 -0.0810 0.5601 1.0000
3.750 0.8165 0.00766 0.00248 -0.0809 0.5523 1.0000
4.000 0.8439 0.00773 0.00259 -0.0808 0.5433 1.0000
4.250 0.8711 0.00784 0.00270 -0.0807 0.5344 1.0000
4.500 0.8981 0.00795 0.00281 -0.0806 0.5247 1.0000
4.750 0.9253 0.00804 0.00296 -0.0805 0.5141 1.0000
5.000 0.9518 0.00817 0.00308 -0.0803 0.4989 1.0000
5.250 0.9775 0.00833 0.00319 -0.0799 0.4724 1.0000
5.500 1.0030 0.00857 0.00335 -0.0795 0.4455 1.0000
5.750 1.0283 0.00885 0.00358 -0.0792 0.4175 1.0000
6.000 1.0517 0.00932 0.00387 -0.0786 0.3711 1.0000
6.500 1.0904 0.01122 0.00503 -0.0766 0.2232 1.0000
6.750 1.1079 0.01238 0.00578 -0.0754 0.1507 1.0000
7.000 1.1253 0.01350 0.00655 -0.0742 0.0917 1.0000
7.250 1.1395 0.01492 0.00757 -0.0725 0.0311 1.0000
7.500 1.1586 0.01580 0.00839 -0.0713 0.0189 1.0000
7.750 1.1793 0.01647 0.00912 -0.0703 0.0166 1.0000
8.000 1.1983 0.01727 0.01001 -0.0691 0.0152 1.0000
8.250 1.2148 0.01825 0.01109 -0.0675 0.0142 1.0000
8.500 1.2328 0.01901 0.01194 -0.0662 0.0135 1.0000
8.750 1.2484 0.01993 0.01294 -0.0645 0.0132 1.0000
9.000 1.2620 0.02093 0.01404 -0.0627 0.0128 1.0000
9.250 1.2733 0.02197 0.01518 -0.0605 0.0125 1.0000
9.500 1.2804 0.02308 0.01639 -0.0576 0.0123 1.0000
9.750 1.2866 0.02429 0.01769 -0.0549 0.0120 1.0000
10.000 1.2924 0.02562 0.01911 -0.0524 0.0118 1.0000
10.250 1.2979 0.02712 0.02070 -0.0501 0.0116 1.0000
10.500 1.3038 0.02874 0.02242 -0.0481 0.0114 1.0000
10.750 1.3100 0.03049 0.02426 -0.0463 0.0112 1.0000
11.000 1.3168 0.03238 0.02624 -0.0446 0.0111 1.0000
11.250 1.3247 0.03434 0.02831 -0.0431 0.0109 1.0000
11.500 1.3336 0.03640 0.03049 -0.0418 0.0108 1.0000
11.750 1.3428 0.03883 0.03306 -0.0405 0.0105 1.0000
12.000 1.3523 0.04186 0.03627 -0.0392 0.0104 1.0000
12.250 1.3586 0.04467 0.03927 -0.0380 0.0103 1.0000
12.500 1.3617 0.04743 0.04222 -0.0369 0.0104 1.0000
12.750 1.3628 0.05008 0.04506 -0.0360 0.0104 1.0000
13.000 1.3611 0.05312 0.04829 -0.0352 0.0105 1.0000
13.250 1.3562 0.05670 0.05209 -0.0347 0.0105 1.0000
13.500 1.3496 0.06032 0.05591 -0.0345 0.0106 1.0000
13.750 1.3037 0.07081 0.06718 -0.0352 0.0124 1.0000
14.000 1.2802 0.07773 0.07436 -0.0370 0.0128 1.0000
14.250 1.2575 0.08476 0.08160 -0.0395 0.0132 1.0000
14.500 1.2347 0.09218 0.08921 -0.0427 0.0135 1.0000
14.750 1.2113 0.10030 0.09750 -0.0468 0.0137 1.0000
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Polar data table (+)
Polar graphs
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