AG11 (ag11-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG11 (ag11-il) Reynolds number: 100,000 Max Cl/Cd: 46.65 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag11-il-100000.txt Download as CSV file: xf-ag11-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG11
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5299 0.11135 0.10648 0.0139 1.0000 0.0528
-8.250 -0.5290 0.10906 0.10425 0.0094 1.0000 0.0536
-8.000 -0.5279 0.10663 0.10189 0.0038 1.0000 0.0540
-7.750 -0.5197 0.10340 0.09867 -0.0042 1.0000 0.0543
-7.500 -0.5120 0.09797 0.09328 -0.0061 1.0000 0.0548
-7.250 -0.5046 0.09273 0.08809 0.0028 1.0000 0.0570
-7.000 -0.4952 0.08904 0.08440 0.0019 1.0000 0.0591
-6.750 -0.4848 0.08530 0.08068 -0.0011 1.0000 0.0614
-6.500 -0.4721 0.08141 0.07679 -0.0058 1.0000 0.0642
-6.250 -0.4465 0.07807 0.07323 -0.0194 1.0000 0.0678
-6.000 -0.4335 0.07276 0.06792 -0.0218 1.0000 0.0690
-5.750 -0.4253 0.06866 0.06396 -0.0186 1.0000 0.0714
-5.500 -0.4094 0.06515 0.06042 -0.0198 1.0000 0.0755
-5.250 -0.3762 0.06189 0.05668 -0.0294 1.0000 0.0827
-5.000 -0.3667 0.05707 0.05212 -0.0272 1.0000 0.0854
-4.750 -0.3465 0.05392 0.04890 -0.0284 1.0000 0.0925
-4.500 -0.3239 0.05009 0.04492 -0.0308 1.0000 0.0999
-4.250 -0.2986 0.04708 0.04163 -0.0332 1.0000 0.1123
-4.000 -0.2756 0.04428 0.03866 -0.0343 1.0000 0.1262
-3.750 -0.2550 0.04118 0.03552 -0.0346 1.0000 0.1411
-3.500 -0.2353 0.03822 0.03261 -0.0343 1.0000 0.1580
-3.250 -0.2157 0.03578 0.03017 -0.0340 1.0000 0.1883
-3.000 -0.1985 0.03362 0.02807 -0.0330 1.0000 0.2344
-2.750 -0.1840 0.03136 0.02598 -0.0310 1.0000 0.2892
-2.500 -0.1664 0.02917 0.02387 -0.0293 1.0000 0.3421
-2.250 -0.0841 0.02461 0.01693 -0.0348 1.0000 0.0986
-2.000 -0.0521 0.02265 0.01425 -0.0329 1.0000 0.0687
-1.750 -0.0263 0.02028 0.01179 -0.0322 1.0000 0.0637
-1.500 0.0003 0.01864 0.00991 -0.0312 1.0000 0.0602
-1.250 0.0264 0.01734 0.00846 -0.0302 1.0000 0.0595
-1.000 0.0515 0.01644 0.00750 -0.0294 1.0000 0.0653
-0.750 0.0770 0.01535 0.00645 -0.0287 1.0000 0.0703
-0.500 0.1023 0.01449 0.00567 -0.0282 1.0000 0.0836
-0.250 0.1310 0.01076 0.00465 -0.0273 1.0000 1.0000
0.000 0.1549 0.01097 0.00447 -0.0268 1.0000 1.0000
0.250 0.1781 0.01124 0.00454 -0.0266 1.0000 1.0000
0.500 0.2006 0.01158 0.00475 -0.0265 1.0000 1.0000
0.750 0.2543 0.01181 0.00483 -0.0323 0.9849 1.0000
1.000 0.3146 0.01185 0.00478 -0.0388 0.9631 1.0000
1.250 0.3694 0.01177 0.00467 -0.0438 0.9392 1.0000
1.500 0.4117 0.01169 0.00456 -0.0458 0.9087 1.0000
1.750 0.4441 0.01165 0.00447 -0.0455 0.8743 1.0000
2.000 0.4698 0.01168 0.00442 -0.0438 0.8365 1.0000
2.250 0.4932 0.01177 0.00439 -0.0417 0.7972 1.0000
2.500 0.5159 0.01192 0.00441 -0.0395 0.7558 1.0000
2.750 0.5388 0.01215 0.00446 -0.0376 0.7119 1.0000
3.000 0.5621 0.01243 0.00456 -0.0359 0.6661 1.0000
3.250 0.5858 0.01276 0.00469 -0.0344 0.6192 1.0000
3.500 0.6095 0.01316 0.00485 -0.0331 0.5722 1.0000
3.750 0.6337 0.01360 0.00512 -0.0320 0.5231 1.0000
4.000 0.6578 0.01410 0.00538 -0.0310 0.4759 1.0000
4.250 0.6820 0.01466 0.00570 -0.0302 0.4307 1.0000
4.500 0.7063 0.01527 0.00609 -0.0294 0.3873 1.0000
4.750 0.7305 0.01593 0.00661 -0.0288 0.3460 1.0000
5.000 0.7549 0.01663 0.00716 -0.0282 0.3070 1.0000
5.250 0.7791 0.01743 0.00778 -0.0277 0.2724 1.0000
5.500 0.8033 0.01827 0.00851 -0.0271 0.2401 1.0000
5.750 0.8275 0.01917 0.00934 -0.0266 0.2121 1.0000
6.000 0.8516 0.02028 0.01027 -0.0261 0.1906 1.0000
6.250 0.8762 0.02133 0.01139 -0.0255 0.1712 1.0000
6.500 0.9005 0.02240 0.01245 -0.0250 0.1553 1.0000
6.750 0.9252 0.02373 0.01387 -0.0245 0.1435 1.0000
7.000 0.9499 0.02525 0.01539 -0.0240 0.1343 1.0000
7.250 0.9742 0.02652 0.01673 -0.0236 0.1248 1.0000
7.500 0.9979 0.02816 0.01869 -0.0230 0.1167 1.0000
7.750 1.0219 0.02998 0.02053 -0.0226 0.1110 1.0000
8.000 1.0436 0.03233 0.02344 -0.0217 0.1060 1.0000
8.250 1.0657 0.03395 0.02524 -0.0211 0.0997 1.0000
8.500 1.0849 0.03683 0.02843 -0.0205 0.0956 1.0000
8.750 1.1002 0.04026 0.03257 -0.0193 0.0927 1.0000
9.000 1.1129 0.04401 0.03688 -0.0183 0.0901 1.0000
9.250 1.1332 0.04585 0.03869 -0.0178 0.0856 1.0000
9.500 1.1387 0.05053 0.04385 -0.0169 0.0832 1.0000
9.750 1.1367 0.05593 0.04988 -0.0159 0.0826 1.0000
10.000 1.1294 0.06181 0.05623 -0.0153 0.0826 1.0000
10.250 1.1178 0.06784 0.06260 -0.0152 0.0830 1.0000
10.500 1.1043 0.07388 0.06886 -0.0155 0.0835 1.0000
10.750 1.0918 0.07990 0.07500 -0.0160 0.0840 1.0000
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Polar data table (+)
Polar graphs
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