AG47c -03f (ag47c03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG47c -03f (ag47c03-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.7 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag47c03-il-1000000-n5.txt Download as CSV file: xf-ag47c03-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG47c -03f
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.6560 0.10282 0.10128 0.0378 1.0000 0.0035
-7.500 -0.6542 0.09823 0.09670 0.0354 1.0000 0.0036
-7.250 -0.6525 0.09369 0.09218 0.0327 1.0000 0.0037
-7.000 -0.6502 0.08927 0.08778 0.0298 1.0000 0.0038
-6.750 -0.6449 0.08445 0.08297 0.0251 1.0000 0.0038
-6.500 -0.6344 0.07891 0.07743 0.0186 1.0000 0.0039
-6.250 -0.6209 0.07290 0.07140 0.0113 1.0000 0.0039
-4.750 -0.4965 0.01928 0.01583 -0.0217 1.0000 0.0037
-4.500 -0.4715 0.01483 0.01068 -0.0216 1.0000 0.0037
-4.250 -0.4450 0.01285 0.00833 -0.0214 1.0000 0.0037
-4.000 -0.4182 0.01155 0.00678 -0.0212 1.0000 0.0038
-3.750 -0.3911 0.01063 0.00570 -0.0210 1.0000 0.0039
-3.500 -0.3639 0.00998 0.00494 -0.0208 1.0000 0.0040
-3.250 -0.3364 0.00896 0.00377 -0.0206 0.9971 0.0046
-3.000 -0.3071 0.00892 0.00334 -0.0206 0.8298 0.0050
-2.750 -0.2817 0.00891 0.00297 -0.0199 0.7488 0.0055
-2.500 -0.2543 0.00869 0.00262 -0.0197 0.7310 0.0059
-2.250 -0.2267 0.00846 0.00230 -0.0196 0.7204 0.0064
-2.000 -0.1989 0.00828 0.00204 -0.0194 0.7129 0.0067
-1.500 -0.1433 0.00786 0.00152 -0.0192 0.7002 0.0104
-1.250 -0.1153 0.00768 0.00132 -0.0191 0.6939 0.0147
-1.000 -0.0873 0.00751 0.00118 -0.0190 0.6860 0.0213
-0.750 -0.0593 0.00736 0.00105 -0.0189 0.6772 0.0332
-0.500 -0.0314 0.00717 0.00093 -0.0188 0.6667 0.0589
-0.250 -0.0035 0.00701 0.00082 -0.0188 0.6536 0.0870
0.000 0.0244 0.00683 0.00073 -0.0188 0.6371 0.1298
0.250 0.0521 0.00663 0.00066 -0.0187 0.6162 0.1927
0.500 0.0798 0.00646 0.00059 -0.0187 0.5910 0.2605
1.000 0.1345 0.00597 0.00053 -0.0188 0.5294 0.4835
1.250 0.1615 0.00570 0.00053 -0.0188 0.4929 0.6165
1.500 0.1875 0.00542 0.00056 -0.0185 0.4551 0.7568
1.750 0.2097 0.00514 0.00059 -0.0170 0.4191 0.8938
2.000 0.2408 0.00519 0.00061 -0.0175 0.3764 1.0000
2.250 0.2685 0.00538 0.00066 -0.0175 0.3386 1.0000
2.500 0.2961 0.00561 0.00072 -0.0174 0.2970 1.0000
2.750 0.3238 0.00582 0.00079 -0.0174 0.2648 1.0000
3.000 0.3514 0.00607 0.00088 -0.0174 0.2245 1.0000
3.250 0.3790 0.00630 0.00097 -0.0174 0.1926 1.0000
3.500 0.4066 0.00653 0.00109 -0.0173 0.1645 1.0000
3.750 0.4341 0.00677 0.00122 -0.0173 0.1367 1.0000
4.000 0.4617 0.00698 0.00134 -0.0173 0.1185 1.0000
4.500 0.5168 0.00740 0.00163 -0.0172 0.0878 1.0000
4.750 0.5444 0.00761 0.00180 -0.0171 0.0762 1.0000
5.000 0.5719 0.00780 0.00197 -0.0170 0.0674 1.0000
5.250 0.5993 0.00802 0.00215 -0.0170 0.0583 1.0000
5.500 0.6267 0.00825 0.00235 -0.0169 0.0507 1.0000
5.750 0.6541 0.00847 0.00257 -0.0169 0.0443 1.0000
6.000 0.6814 0.00872 0.00281 -0.0168 0.0382 1.0000
6.250 0.7086 0.00897 0.00304 -0.0167 0.0330 1.0000
6.500 0.7357 0.00924 0.00331 -0.0166 0.0278 1.0000
6.750 0.7628 0.00951 0.00360 -0.0166 0.0244 1.0000
7.000 0.7897 0.00985 0.00393 -0.0165 0.0198 1.0000
7.250 0.8167 0.01012 0.00425 -0.0164 0.0182 1.0000
7.500 0.8435 0.01046 0.00459 -0.0163 0.0159 1.0000
7.750 0.8699 0.01089 0.00505 -0.0161 0.0129 1.0000
8.000 0.8966 0.01122 0.00542 -0.0160 0.0120 1.0000
8.250 0.9231 0.01159 0.00586 -0.0159 0.0110 1.0000
8.500 0.9493 0.01201 0.00632 -0.0157 0.0100 1.0000
8.750 0.9753 0.01252 0.00687 -0.0156 0.0089 1.0000
9.000 1.0008 0.01316 0.00760 -0.0154 0.0079 1.0000
9.250 1.0268 0.01357 0.00808 -0.0152 0.0075 1.0000
9.500 1.0524 0.01408 0.00867 -0.0151 0.0071 1.0000
9.750 1.0779 0.01460 0.00929 -0.0149 0.0066 1.0000
10.000 1.1031 0.01513 0.00988 -0.0147 0.0061 1.0000
10.250 1.1281 0.01573 0.01053 -0.0146 0.0055 1.0000
10.500 1.1516 0.01672 0.01165 -0.0143 0.0048 1.0000
10.750 1.1762 0.01731 0.01233 -0.0141 0.0046 1.0000
11.000 1.2004 0.01799 0.01312 -0.0139 0.0044 1.0000
11.250 1.2241 0.01874 0.01399 -0.0136 0.0041 1.0000
11.500 1.2474 0.01954 0.01490 -0.0134 0.0038 1.0000
11.750 1.2704 0.02037 0.01585 -0.0131 0.0036 1.0000
12.000 1.2928 0.02126 0.01685 -0.0128 0.0033 1.0000
12.250 1.3142 0.02234 0.01804 -0.0125 0.0030 1.0000
12.500 1.3326 0.02401 0.01992 -0.0121 0.0027 1.0000
12.750 1.3516 0.02540 0.02147 -0.0117 0.0026 1.0000
13.000 1.3702 0.02676 0.02301 -0.0113 0.0025 1.0000
13.250 1.3871 0.02831 0.02474 -0.0109 0.0024 1.0000
13.500 1.4023 0.03002 0.02664 -0.0105 0.0023 1.0000
13.750 1.4151 0.03197 0.02879 -0.0101 0.0022 1.0000
14.000 1.4248 0.03419 0.03122 -0.0097 0.0021 1.0000
14.250 1.4310 0.03667 0.03389 -0.0093 0.0021 1.0000
14.500 1.4305 0.03957 0.03699 -0.0091 0.0020 1.0000
14.750 1.4166 0.04397 0.04159 -0.0109 0.0020 1.0000
15.000 1.3893 0.05367 0.05155 -0.0203 0.0020 1.0000
15.250 1.2992 0.08053 0.07876 -0.0399 0.0023 1.0000
15.500 1.1797 0.10983 0.10815 -0.0555 0.0026 1.0000
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Polar data table (+)
Polar graphs
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