E178 (8.69%) (e178-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E178 (8.69%) (e178-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.06 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e178-il-1000000.txt Download as CSV file: xf-e178-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E178 (8.69%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4078 0.12422 0.12280 0.0065 1.0000 0.0079
-11.000 -0.4042 0.12006 0.11864 0.0047 1.0000 0.0087
-10.750 -0.4841 0.12054 0.11895 0.0038 1.0000 0.0076
-10.500 -0.4794 0.11670 0.11512 0.0021 1.0000 0.0076
-10.250 -0.4746 0.11285 0.11128 0.0003 1.0000 0.0083
-6.500 -0.4441 0.03178 0.02897 -0.0455 0.8054 0.0084
-6.250 -0.4421 0.01951 0.01544 -0.0443 0.7936 0.0079
-6.000 -0.4184 0.01772 0.01331 -0.0438 0.7812 0.0087
-5.750 -0.3927 0.01681 0.01216 -0.0434 0.7696 0.0092
-5.250 -0.3444 0.01321 0.00794 -0.0425 0.7492 0.0106
-5.000 -0.3178 0.01270 0.00735 -0.0423 0.7396 0.0113
-4.750 -0.2907 0.01239 0.00695 -0.0422 0.7309 0.0123
-4.500 -0.2634 0.01206 0.00653 -0.0421 0.7223 0.0135
-4.250 -0.2361 0.01161 0.00597 -0.0419 0.7145 0.0142
-4.000 -0.2087 0.01127 0.00553 -0.0417 0.7069 0.0147
-3.750 -0.1825 0.01031 0.00443 -0.0414 0.7000 0.0153
-3.500 -0.1567 0.00935 0.00332 -0.0410 0.6932 0.0172
-3.250 -0.1293 0.00899 0.00289 -0.0408 0.6867 0.0185
-3.000 -0.1017 0.00870 0.00252 -0.0407 0.6803 0.0195
-2.750 -0.0739 0.00845 0.00220 -0.0406 0.6743 0.0203
-2.500 -0.0461 0.00823 0.00191 -0.0405 0.6682 0.0212
-2.250 -0.0182 0.00808 0.00168 -0.0404 0.6626 0.0224
-2.000 0.0099 0.00784 0.00142 -0.0403 0.6568 0.0287
-1.750 0.0371 0.00750 0.00125 -0.0403 0.6513 0.0815
-1.500 0.0646 0.00721 0.00114 -0.0403 0.6461 0.1406
-1.250 0.0919 0.00689 0.00106 -0.0403 0.6405 0.2195
-1.000 0.1190 0.00663 0.00100 -0.0403 0.6353 0.2986
-0.750 0.1461 0.00627 0.00096 -0.0403 0.6301 0.4022
-0.500 0.1723 0.00586 0.00093 -0.0401 0.6248 0.5382
-0.250 0.1974 0.00542 0.00093 -0.0397 0.6198 0.6881
0.000 0.2184 0.00487 0.00096 -0.0379 0.6146 0.8688
0.250 0.2644 0.00474 0.00098 -0.0415 0.6091 0.9847
0.500 0.3104 0.00475 0.00095 -0.0455 0.6035 0.9993
0.750 0.3388 0.00479 0.00094 -0.0456 0.5976 1.0000
1.000 0.3654 0.00484 0.00094 -0.0453 0.5911 1.0000
1.250 0.3920 0.00488 0.00094 -0.0450 0.5838 1.0000
1.500 0.4188 0.00493 0.00096 -0.0447 0.5773 1.0000
1.750 0.4455 0.00498 0.00098 -0.0445 0.5700 1.0000
2.000 0.4724 0.00503 0.00100 -0.0442 0.5626 1.0000
2.250 0.4992 0.00510 0.00103 -0.0440 0.5547 1.0000
2.500 0.5262 0.00515 0.00108 -0.0438 0.5467 1.0000
2.750 0.5531 0.00523 0.00113 -0.0436 0.5380 1.0000
3.000 0.5803 0.00530 0.00118 -0.0434 0.5289 1.0000
3.250 0.6074 0.00537 0.00124 -0.0432 0.5201 1.0000
3.500 0.6344 0.00547 0.00132 -0.0431 0.5096 1.0000
3.750 0.6615 0.00558 0.00140 -0.0429 0.4975 1.0000
4.000 0.6885 0.00569 0.00149 -0.0428 0.4839 1.0000
4.250 0.7156 0.00581 0.00159 -0.0427 0.4684 1.0000
4.500 0.7426 0.00595 0.00171 -0.0425 0.4522 1.0000
4.750 0.7691 0.00615 0.00185 -0.0424 0.4279 1.0000
5.000 0.7953 0.00642 0.00201 -0.0422 0.3954 1.0000
5.250 0.8193 0.00702 0.00231 -0.0418 0.3241 1.0000
5.500 0.8419 0.00785 0.00276 -0.0413 0.2413 1.0000
5.750 0.8645 0.00865 0.00321 -0.0409 0.1708 1.0000
6.000 0.8882 0.00928 0.00361 -0.0405 0.1250 1.0000
6.250 0.9119 0.00986 0.00402 -0.0401 0.0895 1.0000
6.500 0.9360 0.01039 0.00442 -0.0397 0.0628 1.0000
6.750 0.9591 0.01102 0.00490 -0.0393 0.0354 1.0000
7.000 0.9797 0.01205 0.00577 -0.0383 0.0085 1.0000
7.250 1.0039 0.01250 0.00628 -0.0379 0.0074 1.0000
7.500 1.0274 0.01303 0.00684 -0.0373 0.0064 1.0000
7.750 1.0497 0.01371 0.00760 -0.0366 0.0058 1.0000
8.000 1.0686 0.01479 0.00883 -0.0354 0.0053 1.0000
8.250 1.0908 0.01538 0.00949 -0.0347 0.0052 1.0000
8.500 1.1121 0.01604 0.01023 -0.0339 0.0050 1.0000
8.750 1.1317 0.01685 0.01113 -0.0329 0.0049 1.0000
9.000 1.1512 0.01763 0.01199 -0.0319 0.0046 1.0000
9.250 1.1687 0.01858 0.01302 -0.0306 0.0044 1.0000
9.500 1.1859 0.01949 0.01401 -0.0294 0.0041 1.0000
9.750 1.2012 0.02052 0.01512 -0.0279 0.0038 1.0000
10.000 1.2137 0.02176 0.01648 -0.0261 0.0038 1.0000
10.250 1.2250 0.02302 0.01783 -0.0243 0.0036 1.0000
10.500 1.2312 0.02442 0.01935 -0.0216 0.0036 1.0000
10.750 1.2352 0.02587 0.02091 -0.0189 0.0036 1.0000
11.000 1.2384 0.02760 0.02280 -0.0164 0.0036 1.0000
11.250 1.2403 0.02965 0.02502 -0.0142 0.0036 1.0000
11.500 1.2409 0.03206 0.02762 -0.0122 0.0036 1.0000
11.750 1.2313 0.03640 0.03234 -0.0097 0.0039 1.0000
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Polar data table (+)
Polar graphs
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