E10(08%) (e228-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E10(08%) (e228-il) Reynolds number: 500,000 Max Cl/Cd: 61.22 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e228-il-500000-n5.txt Download as CSV file: xf-e228-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9001 0.10192 0.09948 0.0111 1.0000 0.0044
-14.250 -0.9400 0.08840 0.08583 0.0032 1.0000 0.0043
-14.000 -0.9699 0.07741 0.07471 -0.0036 1.0000 0.0042
-13.750 -0.9998 0.06683 0.06395 -0.0107 1.0000 0.0041
-13.500 -1.0203 0.05864 0.05557 -0.0165 1.0000 0.0042
-13.250 -1.0401 0.05154 0.04828 -0.0213 1.0000 0.0042
-13.000 -1.0573 0.04587 0.04241 -0.0245 1.0000 0.0042
-12.750 -1.0611 0.04265 0.03904 -0.0256 1.0000 0.0042
-12.500 -1.0745 0.03888 0.03507 -0.0258 1.0000 0.0042
-12.250 -1.0789 0.03645 0.03246 -0.0249 1.0000 0.0043
-12.000 -1.0852 0.03410 0.02992 -0.0230 1.0000 0.0044
-11.750 -1.0878 0.03220 0.02783 -0.0205 1.0000 0.0044
-11.500 -1.0890 0.03043 0.02589 -0.0175 1.0000 0.0045
-11.250 -1.0901 0.02820 0.02343 -0.0146 1.0000 0.0047
-11.000 -1.0823 0.02651 0.02157 -0.0126 1.0000 0.0049
-10.750 -1.0698 0.02516 0.02004 -0.0111 1.0000 0.0050
-10.500 -1.0533 0.02416 0.01893 -0.0099 1.0000 0.0053
-10.250 -1.0352 0.02327 0.01794 -0.0088 1.0000 0.0055
-10.000 -1.0173 0.02227 0.01682 -0.0077 1.0000 0.0058
-9.750 -0.9979 0.02142 0.01586 -0.0068 1.0000 0.0062
-9.500 -0.9783 0.02052 0.01485 -0.0058 1.0000 0.0066
-9.250 -0.9582 0.01966 0.01386 -0.0048 1.0000 0.0071
-9.000 -0.9374 0.01886 0.01294 -0.0039 1.0000 0.0074
-8.750 -0.9153 0.01821 0.01220 -0.0032 1.0000 0.0077
-8.500 -0.8958 0.01722 0.01112 -0.0021 1.0000 0.0087
-8.250 -0.8726 0.01672 0.01058 -0.0016 1.0000 0.0095
-8.000 -0.8492 0.01621 0.01002 -0.0010 1.0000 0.0105
-7.750 -0.8261 0.01567 0.00940 -0.0003 1.0000 0.0113
-7.500 -0.8027 0.01516 0.00881 0.0004 1.0000 0.0120
-7.250 -0.7791 0.01469 0.00827 0.0010 1.0000 0.0124
-7.000 -0.7581 0.01389 0.00737 0.0021 1.0000 0.0137
-6.750 -0.7351 0.01340 0.00687 0.0028 1.0000 0.0151
-6.500 -0.7120 0.01300 0.00642 0.0036 1.0000 0.0163
-6.250 -0.6812 0.01258 0.00594 0.0027 0.9901 0.0176
-6.000 -0.6486 0.01214 0.00543 0.0015 0.9802 0.0191
-5.750 -0.6168 0.01169 0.00494 0.0005 0.9700 0.0218
-5.500 -0.5866 0.01134 0.00454 -0.0001 0.9587 0.0247
-5.250 -0.5589 0.01097 0.00418 -0.0001 0.9465 0.0334
-5.000 -0.5335 0.01059 0.00385 0.0004 0.9338 0.0509
-4.750 -0.5093 0.01022 0.00356 0.0011 0.9211 0.0734
-4.500 -0.4854 0.00987 0.00329 0.0019 0.9084 0.1002
-4.250 -0.4614 0.00954 0.00305 0.0026 0.8960 0.1281
-4.000 -0.4367 0.00928 0.00282 0.0033 0.8837 0.1526
-3.750 -0.4123 0.00897 0.00260 0.0040 0.8713 0.1863
-3.500 -0.3873 0.00871 0.00242 0.0045 0.8585 0.2183
-3.250 -0.3620 0.00845 0.00225 0.0051 0.8457 0.2523
-3.000 -0.3370 0.00817 0.00208 0.0056 0.8327 0.2946
-2.750 -0.3120 0.00789 0.00192 0.0061 0.8194 0.3411
-2.500 -0.2863 0.00769 0.00180 0.0066 0.8058 0.3770
-2.250 -0.2603 0.00752 0.00168 0.0070 0.7918 0.4082
-2.000 -0.2342 0.00737 0.00158 0.0074 0.7776 0.4388
-1.750 -0.2081 0.00723 0.00148 0.0078 0.7631 0.4702
-1.500 -0.1819 0.00710 0.00140 0.0082 0.7482 0.5019
-1.250 -0.1557 0.00698 0.00133 0.0086 0.7332 0.5337
-1.000 -0.1296 0.00687 0.00127 0.0091 0.7176 0.5660
-0.750 -0.1035 0.00677 0.00122 0.0095 0.7016 0.5990
-0.500 -0.0774 0.00668 0.00119 0.0099 0.6848 0.6315
-0.250 -0.0514 0.00659 0.00116 0.0104 0.6675 0.6641
0.000 -0.0254 0.00653 0.00115 0.0109 0.6495 0.6956
0.250 0.0006 0.00649 0.00115 0.0114 0.6315 0.7264
0.500 0.0267 0.00645 0.00116 0.0119 0.6126 0.7556
0.750 0.0528 0.00643 0.00118 0.0124 0.5931 0.7838
1.000 0.0790 0.00644 0.00121 0.0129 0.5736 0.8109
1.250 0.1055 0.00646 0.00125 0.0134 0.5529 0.8366
1.500 0.1323 0.00650 0.00132 0.0138 0.5320 0.8613
1.750 0.1601 0.00658 0.00138 0.0139 0.5100 0.8849
2.000 0.1900 0.00668 0.00147 0.0136 0.4871 0.9055
2.250 0.2221 0.00684 0.00158 0.0128 0.4615 0.9228
2.500 0.2558 0.00703 0.00170 0.0116 0.4338 0.9361
2.750 0.2896 0.00723 0.00181 0.0103 0.4054 0.9465
3.000 0.3215 0.00745 0.00194 0.0094 0.3773 0.9561
3.250 0.3553 0.00769 0.00209 0.0080 0.3466 0.9629
3.500 0.3862 0.00793 0.00224 0.0073 0.3187 0.9704
3.750 0.4203 0.00819 0.00240 0.0058 0.2875 0.9753
4.000 0.4507 0.00848 0.00258 0.0051 0.2573 0.9816
4.250 0.4851 0.00879 0.00279 0.0035 0.2258 0.9850
4.500 0.5185 0.00912 0.00300 0.0020 0.1923 0.9886
4.750 0.5507 0.00948 0.00324 0.0008 0.1608 0.9924
5.000 0.5837 0.00985 0.00349 -0.0006 0.1321 0.9953
5.250 0.6174 0.01022 0.00376 -0.0022 0.1074 0.9981
5.500 0.6483 0.01059 0.00408 -0.0031 0.0873 1.0000
5.750 0.6706 0.01096 0.00438 -0.0022 0.0698 1.0000
6.000 0.6925 0.01138 0.00471 -0.0013 0.0532 1.0000
6.250 0.7147 0.01176 0.00505 -0.0004 0.0422 1.0000
6.500 0.7371 0.01212 0.00540 0.0005 0.0342 1.0000
6.750 0.7592 0.01252 0.00578 0.0014 0.0271 1.0000
7.000 0.7808 0.01298 0.00623 0.0024 0.0201 1.0000
7.250 0.8024 0.01343 0.00668 0.0034 0.0151 1.0000
7.500 0.8240 0.01390 0.00717 0.0044 0.0115 1.0000
7.750 0.8449 0.01446 0.00775 0.0055 0.0090 1.0000
8.000 0.8661 0.01497 0.00833 0.0066 0.0080 1.0000
8.250 0.8868 0.01552 0.00895 0.0077 0.0072 1.0000
8.500 0.9069 0.01615 0.00966 0.0089 0.0066 1.0000
8.750 0.9252 0.01697 0.01058 0.0103 0.0059 1.0000
9.000 0.9427 0.01785 0.01157 0.0118 0.0055 1.0000
9.250 0.9618 0.01850 0.01231 0.0131 0.0053 1.0000
9.500 0.9804 0.01920 0.01310 0.0143 0.0050 1.0000
9.750 0.9983 0.01995 0.01394 0.0156 0.0047 1.0000
10.000 1.0142 0.02088 0.01499 0.0171 0.0046 1.0000
10.250 1.0295 0.02184 0.01606 0.0187 0.0044 1.0000
10.500 1.0441 0.02280 0.01713 0.0202 0.0042 1.0000
10.750 1.0570 0.02387 0.01835 0.0220 0.0041 1.0000
11.000 1.0686 0.02497 0.01957 0.0237 0.0040 1.0000
11.250 1.0776 0.02618 0.02091 0.0257 0.0039 1.0000
11.500 1.0808 0.02745 0.02230 0.0286 0.0038 1.0000
11.750 1.0836 0.02872 0.02369 0.0310 0.0037 1.0000
12.000 1.0839 0.03036 0.02547 0.0332 0.0037 1.0000
12.250 1.0828 0.03228 0.02751 0.0347 0.0035 1.0000
12.500 1.0816 0.03444 0.02982 0.0356 0.0035 1.0000
12.750 1.0778 0.03710 0.03263 0.0360 0.0034 1.0000
13.000 1.0680 0.04073 0.03644 0.0355 0.0033 1.0000
13.250 1.0559 0.04511 0.04100 0.0341 0.0033 1.0000
13.500 1.0571 0.04809 0.04411 0.0329 0.0035 1.0000
13.750 1.0351 0.05472 0.05094 0.0293 0.0033 1.0000
14.000 1.0282 0.05950 0.05586 0.0265 0.0033 1.0000
14.250 1.0063 0.06711 0.06365 0.0220 0.0032 1.0000
14.500 0.9942 0.07334 0.07001 0.0182 0.0033 1.0000
14.750 0.9836 0.07950 0.07629 0.0147 0.0034 1.0000
15.000 0.9654 0.08729 0.08421 0.0102 0.0034 1.0000
15.250 0.9427 0.09633 0.09339 0.0052 0.0034 1.0000
15.500 0.9228 0.10508 0.10227 0.0005 0.0035 1.0000
15.750 0.8974 0.11545 0.11274 -0.0050 0.0035 1.0000
16.000 0.8696 0.12689 0.12430 -0.0108 0.0035 1.0000
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Polar data table (+)
Polar graphs
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