E474 (14.09%) (e474-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E474 (14.09%) (e474-il) Reynolds number: 200,000 Max Cl/Cd: 45.33 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e474-il-200000.txt Download as CSV file: xf-e474-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E474 (14.09%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.9940 0.12317 0.11888 -0.0091 1.0000 0.0580
-18.250 -1.0516 0.10822 0.10365 -0.0182 1.0000 0.0583
-18.000 -1.0877 0.09793 0.09312 -0.0245 1.0000 0.0591
-17.750 -1.0758 0.09691 0.09226 -0.0242 1.0000 0.0621
-17.500 -1.0883 0.09126 0.08656 -0.0274 1.0000 0.0642
-17.250 -1.1128 0.08369 0.07883 -0.0319 1.0000 0.0658
-17.000 -1.1386 0.07617 0.07112 -0.0363 1.0000 0.0672
-16.750 -1.1631 0.06910 0.06382 -0.0405 1.0000 0.0684
-16.500 -1.1639 0.06623 0.06108 -0.0413 1.0000 0.0714
-16.250 -1.1758 0.06146 0.05623 -0.0439 1.0000 0.0735
-16.000 -1.1906 0.05637 0.05100 -0.0466 1.0000 0.0756
-15.750 -1.2079 0.05119 0.04558 -0.0494 1.0000 0.0778
-15.500 -1.2140 0.04783 0.04222 -0.0503 1.0000 0.0804
-15.250 -1.2194 0.04474 0.03909 -0.0513 1.0000 0.0830
-15.000 -1.2258 0.04177 0.03599 -0.0518 1.0000 0.0858
-14.750 -1.2347 0.03891 0.03290 -0.0518 1.0000 0.0886
-14.500 -1.2356 0.03689 0.03091 -0.0510 1.0000 0.0917
-14.250 -1.2358 0.03529 0.02926 -0.0498 1.0000 0.0949
-14.000 -1.2369 0.03376 0.02759 -0.0481 1.0000 0.0982
-13.750 -1.2384 0.03228 0.02593 -0.0460 1.0000 0.1016
-13.500 -1.2329 0.03131 0.02502 -0.0439 1.0000 0.1050
-13.250 -1.2293 0.03049 0.02412 -0.0414 1.0000 0.1088
-13.000 -1.2292 0.02960 0.02301 -0.0381 1.0000 0.1124
-12.750 -1.2213 0.02878 0.02226 -0.0355 1.0000 0.1162
-12.500 -1.2137 0.02834 0.02180 -0.0327 1.0000 0.1201
-12.250 -1.2065 0.02775 0.02102 -0.0299 1.0000 0.1245
-12.000 -1.1943 0.02707 0.02035 -0.0278 1.0000 0.1288
-11.750 -1.1804 0.02682 0.02010 -0.0257 1.0000 0.1332
-11.500 -1.1700 0.02638 0.01946 -0.0230 1.0000 0.1380
-11.250 -1.1544 0.02579 0.01891 -0.0212 1.0000 0.1424
-11.000 -1.1379 0.02556 0.01869 -0.0193 1.0000 0.1467
-10.750 -1.1248 0.02515 0.01809 -0.0169 1.0000 0.1513
-10.500 -1.1085 0.02450 0.01740 -0.0151 1.0000 0.1555
-10.250 -1.0899 0.02427 0.01721 -0.0135 1.0000 0.1595
-10.000 -1.0738 0.02392 0.01675 -0.0115 1.0000 0.1641
-9.750 -1.0586 0.02335 0.01601 -0.0093 1.0000 0.1683
-9.500 -1.0382 0.02297 0.01572 -0.0080 1.0000 0.1722
-9.250 -1.0198 0.02271 0.01542 -0.0063 1.0000 0.1765
-9.000 -1.0038 0.02234 0.01485 -0.0041 1.0000 0.1811
-8.750 -0.9840 0.02176 0.01430 -0.0027 1.0000 0.1851
-8.500 -0.9638 0.02149 0.01405 -0.0012 1.0000 0.1891
-8.250 -0.9453 0.02118 0.01364 0.0005 1.0000 0.1938
-8.000 -0.9274 0.02073 0.01302 0.0024 1.0000 0.1981
-7.750 -0.9059 0.02026 0.01265 0.0035 1.0000 0.2020
-7.500 -0.8855 0.01997 0.01234 0.0050 1.0000 0.2063
-7.250 -0.8664 0.01967 0.01190 0.0067 1.0000 0.2111
-7.000 -0.8458 0.01913 0.01132 0.0080 1.0000 0.2152
-6.750 -0.8243 0.01879 0.01104 0.0092 1.0000 0.2193
-6.500 -0.8036 0.01851 0.01071 0.0106 1.0000 0.2239
-6.250 -0.7836 0.01827 0.01031 0.0122 1.0000 0.2285
-6.000 -0.7614 0.01771 0.00983 0.0132 1.0000 0.2326
-5.750 -0.7399 0.01742 0.00957 0.0145 1.0000 0.2370
-5.500 -0.7188 0.01718 0.00926 0.0158 1.0000 0.2420
-5.250 -0.6974 0.01682 0.00884 0.0171 1.0000 0.2465
-5.000 -0.6754 0.01647 0.00857 0.0181 1.0000 0.2507
-4.750 -0.6538 0.01624 0.00834 0.0193 1.0000 0.2555
-4.500 -0.6325 0.01608 0.00809 0.0206 1.0000 0.2607
-4.250 -0.6106 0.01571 0.00780 0.0217 1.0000 0.2654
-4.000 -0.5890 0.01551 0.00764 0.0228 1.0000 0.2702
-3.750 -0.5678 0.01536 0.00746 0.0240 1.0000 0.2755
-3.500 -0.5280 0.01513 0.00729 0.0215 0.9952 0.2820
-3.250 -0.4790 0.01498 0.00720 0.0172 0.9869 0.2901
-3.000 -0.4296 0.01470 0.00697 0.0130 0.9788 0.2978
-2.750 -0.3808 0.01444 0.00679 0.0089 0.9697 0.3068
-2.500 -0.3367 0.01408 0.00651 0.0059 0.9591 0.3157
-2.250 -0.2890 0.01374 0.00623 0.0023 0.9486 0.3259
-2.000 -0.2383 0.01325 0.00590 -0.0018 0.9383 0.3371
-1.750 -0.1983 0.01281 0.00555 -0.0037 0.9222 0.3491
-1.500 -0.1662 0.01243 0.00524 -0.0038 0.8969 0.3617
-1.250 -0.1305 0.01196 0.00488 -0.0046 0.8609 0.3764
-1.000 -0.0886 0.01154 0.00443 -0.0065 0.7973 0.3963
-0.750 -0.0600 0.01143 0.00413 -0.0057 0.7127 0.4170
-0.500 -0.0391 0.01152 0.00400 -0.0038 0.6339 0.4410
-0.250 -0.0196 0.01162 0.00393 -0.0019 0.5665 0.4711
0.000 0.0000 0.01166 0.00391 0.0000 0.5122 0.5122
0.250 0.0196 0.01162 0.00393 0.0019 0.4711 0.5663
0.500 0.0391 0.01152 0.00400 0.0038 0.4408 0.6339
0.750 0.0600 0.01143 0.00413 0.0057 0.4169 0.7127
1.000 0.0886 0.01154 0.00443 0.0065 0.3963 0.7974
1.250 0.1304 0.01196 0.00488 0.0047 0.3765 0.8608
1.500 0.1662 0.01243 0.00523 0.0038 0.3617 0.8968
1.750 0.1982 0.01280 0.00555 0.0037 0.3492 0.9222
2.000 0.2382 0.01325 0.00590 0.0018 0.3373 0.9382
2.250 0.2890 0.01373 0.00623 -0.0023 0.3258 0.9486
2.500 0.3366 0.01407 0.00651 -0.0059 0.3157 0.9591
2.750 0.3810 0.01444 0.00679 -0.0090 0.3068 0.9697
3.000 0.4295 0.01470 0.00696 -0.0129 0.2977 0.9789
3.250 0.4793 0.01497 0.00719 -0.0173 0.2900 0.9870
3.500 0.5283 0.01513 0.00729 -0.0215 0.2820 0.9953
3.750 0.5677 0.01536 0.00746 -0.0240 0.2754 1.0000
4.000 0.5889 0.01551 0.00764 -0.0228 0.2702 1.0000
4.250 0.6105 0.01571 0.00780 -0.0217 0.2654 1.0000
4.500 0.6325 0.01608 0.00809 -0.0206 0.2607 1.0000
4.750 0.6537 0.01624 0.00834 -0.0193 0.2556 1.0000
5.000 0.6753 0.01647 0.00856 -0.0181 0.2507 1.0000
5.250 0.6973 0.01682 0.00884 -0.0170 0.2466 1.0000
5.500 0.7187 0.01717 0.00925 -0.0158 0.2420 1.0000
5.750 0.7398 0.01741 0.00956 -0.0145 0.2370 1.0000
6.000 0.7614 0.01770 0.00983 -0.0132 0.2326 1.0000
6.250 0.7836 0.01827 0.01031 -0.0122 0.2285 1.0000
6.500 0.8035 0.01851 0.01071 -0.0106 0.2240 1.0000
6.750 0.8242 0.01879 0.01104 -0.0092 0.2193 1.0000
7.000 0.8457 0.01913 0.01133 -0.0080 0.2153 1.0000
7.250 0.8664 0.01968 0.01190 -0.0067 0.2111 1.0000
7.500 0.8855 0.01997 0.01234 -0.0050 0.2063 1.0000
7.750 0.9058 0.02026 0.01265 -0.0035 0.2020 1.0000
8.000 0.9274 0.02072 0.01301 -0.0024 0.1982 1.0000
8.250 0.9453 0.02118 0.01364 -0.0005 0.1938 1.0000
8.500 0.9638 0.02148 0.01404 0.0012 0.1891 1.0000
8.750 0.9840 0.02175 0.01429 0.0027 0.1851 1.0000
9.000 1.0038 0.02234 0.01485 0.0041 0.1811 1.0000
9.250 1.0197 0.02270 0.01541 0.0063 0.1766 1.0000
9.500 1.0382 0.02298 0.01572 0.0080 0.1722 1.0000
9.750 1.0585 0.02335 0.01600 0.0093 0.1683 1.0000
10.000 1.0738 0.02393 0.01676 0.0114 0.1641 1.0000
10.250 1.0899 0.02427 0.01722 0.0135 0.1595 1.0000
10.500 1.1085 0.02450 0.01740 0.0151 0.1555 1.0000
10.750 1.1249 0.02515 0.01809 0.0169 0.1514 1.0000
11.000 1.1380 0.02557 0.01870 0.0193 0.1467 1.0000
11.250 1.1545 0.02579 0.01890 0.0212 0.1424 1.0000
11.500 1.1701 0.02638 0.01947 0.0230 0.1380 1.0000
11.750 1.1805 0.02682 0.02010 0.0256 0.1332 1.0000
12.000 1.1944 0.02706 0.02033 0.0277 0.1288 1.0000
12.250 1.2066 0.02773 0.02101 0.0298 0.1245 1.0000
12.500 1.2139 0.02832 0.02178 0.0327 0.1200 1.0000
12.750 1.2217 0.02876 0.02224 0.0355 0.1161 1.0000
13.000 1.2296 0.02959 0.02301 0.0380 0.1123 1.0000
13.250 1.2298 0.03048 0.02411 0.0413 0.1088 1.0000
13.500 1.2335 0.03130 0.02501 0.0438 0.1050 1.0000
13.750 1.2392 0.03229 0.02592 0.0459 0.1015 1.0000
14.000 1.2376 0.03377 0.02760 0.0481 0.0982 1.0000
14.250 1.2364 0.03528 0.02925 0.0497 0.0947 1.0000
14.500 1.2364 0.03688 0.03088 0.0509 0.0916 1.0000
14.750 1.2353 0.03891 0.03291 0.0517 0.0885 1.0000
15.000 1.2270 0.04174 0.03597 0.0517 0.0858 1.0000
15.250 1.2205 0.04471 0.03906 0.0511 0.0829 1.0000
15.500 1.2153 0.04777 0.04215 0.0502 0.0803 1.0000
15.750 1.2084 0.05124 0.04564 0.0491 0.0777 1.0000
16.000 1.1925 0.05627 0.05089 0.0465 0.0757 1.0000
16.250 1.1777 0.06136 0.05613 0.0438 0.0735 1.0000
16.500 1.1657 0.06614 0.06098 0.0411 0.0712 1.0000
16.750 1.1655 0.06892 0.06363 0.0404 0.0684 1.0000
17.000 1.1396 0.07622 0.07117 0.0360 0.0672 1.0000
17.250 1.1148 0.08358 0.07873 0.0317 0.0658 1.0000
17.500 1.0906 0.09111 0.08641 0.0273 0.0642 1.0000
17.750 1.0789 0.09659 0.09193 0.0243 0.0620 1.0000
18.000 1.0896 0.09783 0.09302 0.0243 0.0591 1.0000
18.250 1.0522 0.10837 0.10380 0.0179 0.0583 1.0000
18.500 0.9936 0.12357 0.11929 0.0086 0.0579 1.0000
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Polar data table (+)
Polar graphs
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