E10(08%) (e228-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E10(08%) (e228-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.59 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e228-il-1000000-n5.txt Download as CSV file: xf-e228-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E10(08%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9647 0.12487 0.12292 0.0236 1.0000 0.0024
-16.250 -1.0211 0.10749 0.10538 0.0136 1.0000 0.0024
-16.000 -1.0665 0.09355 0.09130 0.0056 1.0000 0.0023
-15.750 -1.0844 0.08554 0.08323 0.0010 1.0000 0.0024
-15.500 -1.1444 0.06936 0.06680 -0.0090 1.0000 0.0023
-15.250 -1.1860 0.05745 0.05466 -0.0170 1.0000 0.0022
-15.000 -1.2038 0.05062 0.04767 -0.0214 1.0000 0.0023
-14.750 -1.2166 0.04529 0.04220 -0.0245 1.0000 0.0023
-14.500 -1.2291 0.04076 0.03751 -0.0264 1.0000 0.0023
-14.250 -1.2391 0.03718 0.03378 -0.0271 1.0000 0.0023
-14.000 -1.2433 0.03464 0.03111 -0.0266 1.0000 0.0023
-13.750 -1.2502 0.03221 0.02854 -0.0252 1.0000 0.0023
-13.500 -1.2518 0.03044 0.02664 -0.0233 1.0000 0.0023
-13.250 -1.2522 0.02891 0.02499 -0.0209 1.0000 0.0023
-13.000 -1.2511 0.02756 0.02350 -0.0180 1.0000 0.0024
-12.750 -1.2454 0.02653 0.02236 -0.0154 1.0000 0.0024
-12.500 -1.2369 0.02536 0.02107 -0.0132 1.0000 0.0024
-12.250 -1.2285 0.02393 0.01948 -0.0111 1.0000 0.0025
-12.000 -1.2176 0.02257 0.01796 -0.0092 1.0000 0.0026
-11.750 -1.2032 0.02142 0.01669 -0.0077 1.0000 0.0028
-11.500 -1.1860 0.02050 0.01567 -0.0065 1.0000 0.0029
-11.250 -1.1670 0.01971 0.01480 -0.0055 1.0000 0.0031
-11.000 -1.1467 0.01903 0.01406 -0.0046 1.0000 0.0033
-10.750 -1.1259 0.01837 0.01333 -0.0038 1.0000 0.0034
-10.500 -1.1045 0.01774 0.01262 -0.0030 1.0000 0.0036
-10.250 -1.0823 0.01719 0.01200 -0.0024 1.0000 0.0039
-10.000 -1.0602 0.01659 0.01134 -0.0017 1.0000 0.0041
-9.750 -1.0374 0.01606 0.01074 -0.0010 1.0000 0.0043
-9.500 -1.0143 0.01555 0.01016 -0.0004 1.0000 0.0044
-9.250 -0.9924 0.01483 0.00936 0.0004 1.0000 0.0049
-9.000 -0.9690 0.01432 0.00882 0.0010 1.0000 0.0055
-8.750 -0.9448 0.01390 0.00839 0.0015 1.0000 0.0060
-8.500 -0.9204 0.01350 0.00795 0.0019 1.0000 0.0066
-8.250 -0.8957 0.01313 0.00754 0.0024 1.0000 0.0072
-8.000 -0.8707 0.01281 0.00718 0.0028 1.0000 0.0076
-7.750 -0.8464 0.01240 0.00672 0.0033 1.0000 0.0082
-7.500 -0.8188 0.01198 0.00629 0.0031 0.9913 0.0092
-7.250 -0.7865 0.01165 0.00595 0.0019 0.9791 0.0102
-7.000 -0.7560 0.01134 0.00559 0.0012 0.9665 0.0111
-6.750 -0.7289 0.01107 0.00527 0.0013 0.9527 0.0117
-6.500 -0.7040 0.01085 0.00499 0.0019 0.9390 0.0121
-6.250 -0.6796 0.01062 0.00470 0.0027 0.9260 0.0124
-6.000 -0.6556 0.01030 0.00430 0.0035 0.9132 0.0142
-5.750 -0.6308 0.01003 0.00400 0.0041 0.9010 0.0157
-5.500 -0.6054 0.00981 0.00371 0.0046 0.8888 0.0168
-5.250 -0.5795 0.00962 0.00346 0.0051 0.8767 0.0178
-5.000 -0.5535 0.00943 0.00321 0.0055 0.8645 0.0197
-4.750 -0.5277 0.00920 0.00297 0.0060 0.8522 0.0252
-4.500 -0.5023 0.00888 0.00270 0.0064 0.8398 0.0431
-4.250 -0.4764 0.00863 0.00248 0.0068 0.8272 0.0597
-4.000 -0.4506 0.00836 0.00225 0.0072 0.8144 0.0818
-3.750 -0.4247 0.00811 0.00206 0.0075 0.8012 0.1070
-3.500 -0.3987 0.00784 0.00188 0.0078 0.7877 0.1375
-3.250 -0.3722 0.00765 0.00172 0.0081 0.7737 0.1602
-3.000 -0.3456 0.00747 0.00158 0.0083 0.7594 0.1851
-2.500 -0.2924 0.00712 0.00133 0.0088 0.7301 0.2415
-2.250 -0.2665 0.00685 0.00121 0.0091 0.7154 0.2926
-2.000 -0.2401 0.00665 0.00112 0.0093 0.7002 0.3348
-1.750 -0.2131 0.00654 0.00103 0.0095 0.6846 0.3614
-1.500 -0.1861 0.00643 0.00097 0.0097 0.6686 0.3890
-1.250 -0.1590 0.00634 0.00091 0.0098 0.6517 0.4155
-1.000 -0.1320 0.00626 0.00086 0.0100 0.6343 0.4432
-0.750 -0.1049 0.00619 0.00082 0.0102 0.6169 0.4709
-0.500 -0.0778 0.00612 0.00079 0.0103 0.5991 0.5000
-0.250 -0.0509 0.00606 0.00076 0.0105 0.5801 0.5306
0.250 0.0029 0.00596 0.00074 0.0109 0.5425 0.5907
0.500 0.0298 0.00592 0.00075 0.0111 0.5232 0.6215
0.750 0.0565 0.00590 0.00076 0.0113 0.5034 0.6509
1.000 0.0832 0.00588 0.00078 0.0116 0.4829 0.6808
1.250 0.1098 0.00589 0.00081 0.0119 0.4620 0.7088
1.500 0.1364 0.00590 0.00085 0.0122 0.4406 0.7363
1.750 0.1628 0.00593 0.00090 0.0125 0.4188 0.7634
2.000 0.1891 0.00598 0.00096 0.0128 0.3945 0.7899
2.250 0.2154 0.00604 0.00104 0.0132 0.3707 0.8160
2.500 0.2415 0.00610 0.00112 0.0136 0.3483 0.8420
2.750 0.2674 0.00619 0.00121 0.0141 0.3232 0.8680
3.000 0.2938 0.00629 0.00131 0.0144 0.2998 0.8927
3.250 0.3212 0.00643 0.00144 0.0146 0.2765 0.9150
3.500 0.3510 0.00662 0.00159 0.0142 0.2514 0.9342
3.750 0.3832 0.00686 0.00175 0.0132 0.2240 0.9482
4.000 0.4156 0.00710 0.00192 0.0121 0.1992 0.9584
4.250 0.4466 0.00739 0.00211 0.0113 0.1708 0.9670
4.500 0.4785 0.00771 0.00231 0.0102 0.1427 0.9727
4.750 0.5094 0.00802 0.00251 0.0094 0.1178 0.9783
5.000 0.5389 0.00832 0.00273 0.0089 0.0970 0.9830
5.250 0.5721 0.00867 0.00298 0.0075 0.0747 0.9853
5.500 0.6045 0.00897 0.00323 0.0063 0.0606 0.9879
5.750 0.6358 0.00930 0.00349 0.0053 0.0465 0.9907
6.000 0.6659 0.00967 0.00379 0.0046 0.0331 0.9935
6.250 0.6984 0.00998 0.00407 0.0034 0.0254 0.9952
6.500 0.7309 0.01032 0.00437 0.0021 0.0191 0.9970
6.750 0.7629 0.01069 0.00471 0.0009 0.0138 0.9987
7.000 0.7939 0.01109 0.00510 -0.0001 0.0089 1.0000
7.250 0.8161 0.01145 0.00547 0.0009 0.0068 1.0000
7.500 0.8384 0.01183 0.00587 0.0019 0.0055 1.0000
7.750 0.8607 0.01218 0.00626 0.0028 0.0051 1.0000
8.000 0.8828 0.01255 0.00667 0.0038 0.0047 1.0000
8.250 0.9046 0.01295 0.00711 0.0048 0.0042 1.0000
8.500 0.9261 0.01340 0.00760 0.0058 0.0039 1.0000
8.750 0.9468 0.01393 0.00820 0.0070 0.0035 1.0000
9.000 0.9665 0.01458 0.00893 0.0082 0.0032 1.0000
9.250 0.9862 0.01522 0.00965 0.0095 0.0031 1.0000
9.500 1.0067 0.01573 0.01022 0.0106 0.0030 1.0000
9.750 1.0268 0.01627 0.01083 0.0117 0.0030 1.0000
10.000 1.0456 0.01693 0.01157 0.0130 0.0029 1.0000
10.250 1.0645 0.01757 0.01228 0.0142 0.0029 1.0000
10.500 1.0831 0.01820 0.01301 0.0155 0.0028 1.0000
10.750 1.1005 0.01895 0.01384 0.0169 0.0027 1.0000
11.000 1.1174 0.01969 0.01467 0.0182 0.0026 1.0000
11.250 1.1326 0.02057 0.01565 0.0198 0.0025 1.0000
11.500 1.1468 0.02147 0.01665 0.0214 0.0025 1.0000
11.750 1.1611 0.02231 0.01757 0.0230 0.0024 1.0000
12.000 1.1717 0.02335 0.01873 0.0249 0.0024 1.0000
12.250 1.1811 0.02426 0.01972 0.0271 0.0022 1.0000
12.500 1.1853 0.02524 0.02080 0.0299 0.0022 1.0000
12.750 1.1886 0.02642 0.02207 0.0323 0.0022 1.0000
13.000 1.1911 0.02782 0.02358 0.0343 0.0021 1.0000
13.250 1.1950 0.02927 0.02514 0.0357 0.0020 1.0000
13.500 1.1859 0.03203 0.02810 0.0370 0.0022 1.0000
13.750 1.1900 0.03388 0.03001 0.0373 0.0020 1.0000
14.000 1.1855 0.03681 0.03309 0.0371 0.0020 1.0000
14.250 1.1876 0.03929 0.03564 0.0365 0.0019 1.0000
14.500 1.1791 0.04332 0.03983 0.0349 0.0019 1.0000
14.750 1.1649 0.04857 0.04525 0.0323 0.0020 1.0000
15.000 1.1544 0.05367 0.05049 0.0295 0.0020 1.0000
15.250 1.1339 0.06072 0.05771 0.0254 0.0020 1.0000
15.500 1.1099 0.06871 0.06588 0.0207 0.0020 1.0000
15.750 1.0951 0.07537 0.07262 0.0169 0.0019 1.0000
16.000 1.0677 0.08450 0.08188 0.0119 0.0019 1.0000
16.250 1.0277 0.09625 0.09383 0.0056 0.0021 1.0000
16.500 0.9998 0.10613 0.10382 0.0005 0.0021 1.0000
16.750 0.9694 0.11692 0.11471 -0.0051 0.0021 1.0000
17.000 0.9345 0.12918 0.12710 -0.0114 0.0021 1.0000
17.250 0.9095 0.13982 0.13782 -0.0168 0.0022 1.0000
17.500 0.8750 0.15352 0.15165 -0.0237 0.0022 1.0000
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Polar data table (+)
Polar graphs
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