AG47c -03f (ag47c03-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG47c -03f (ag47c03-il) Reynolds number: 50,000 Max Cl/Cd: 30.29 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag47c03-il-50000.txt Download as CSV file: xf-ag47c03-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.6228 0.10839 0.10195 0.0329 1.0000 0.1844
-6.750 -0.6166 0.10423 0.09786 0.0323 1.0000 0.1910
-6.500 -0.6221 0.10218 0.09590 0.0271 1.0000 0.2001
-6.250 -0.6078 0.09728 0.09102 0.0296 1.0000 0.2110
-6.000 -0.6002 0.09331 0.08710 0.0286 1.0000 0.2218
-5.750 -0.5931 0.08952 0.08337 0.0270 1.0000 0.2348
-5.500 -0.5847 0.08579 0.07968 0.0257 1.0000 0.2504
-5.250 -0.5807 0.08264 0.07658 0.0199 1.0000 0.2709
-5.000 -0.5665 0.07829 0.07224 0.0239 1.0000 0.2894
-4.750 -0.5572 0.07474 0.06873 0.0234 1.0000 0.3154
-4.500 -0.5460 0.07124 0.06528 0.0256 1.0000 0.3455
-4.250 -0.5366 0.06807 0.06219 0.0291 1.0000 0.3872
-3.750 -0.5176 0.06216 0.05643 0.0427 1.0000 0.5003
-3.250 -0.3677 0.03996 0.03162 -0.0231 1.0000 0.1433
-3.000 -0.3357 0.03542 0.02654 -0.0243 1.0000 0.1257
-2.750 -0.3022 0.03173 0.02198 -0.0250 1.0000 0.1156
-2.500 -0.2721 0.02872 0.01847 -0.0249 1.0000 0.1152
-2.250 -0.2438 0.02624 0.01576 -0.0247 1.0000 0.1243
-2.000 -0.2130 0.02401 0.01293 -0.0241 1.0000 0.1306
-1.750 -0.1850 0.02188 0.01081 -0.0235 1.0000 0.1494
-1.500 -0.1567 0.01994 0.00886 -0.0225 1.0000 0.1792
-1.250 -0.1289 0.01772 0.00709 -0.0217 1.0000 0.2654
-1.000 -0.0967 0.01355 0.00530 -0.0192 1.0000 1.0000
-0.750 -0.0697 0.01349 0.00470 -0.0188 1.0000 1.0000
-0.500 -0.0431 0.01344 0.00422 -0.0186 1.0000 1.0000
-0.250 -0.0166 0.01341 0.00389 -0.0183 1.0000 1.0000
0.000 0.0097 0.01339 0.00363 -0.0181 1.0000 1.0000
0.250 0.0360 0.01339 0.00344 -0.0178 1.0000 1.0000
0.500 0.0621 0.01340 0.00328 -0.0176 1.0000 1.0000
0.750 0.0880 0.01343 0.00321 -0.0174 1.0000 1.0000
1.000 0.1136 0.01348 0.00319 -0.0173 1.0000 1.0000
1.250 0.1389 0.01355 0.00323 -0.0171 1.0000 1.0000
1.500 0.1637 0.01365 0.00333 -0.0169 1.0000 1.0000
1.750 0.1875 0.01379 0.00351 -0.0168 1.0000 1.0000
2.000 0.2102 0.01401 0.00378 -0.0168 1.0000 1.0000
2.250 0.2316 0.01432 0.00414 -0.0168 1.0000 1.0000
2.500 0.2520 0.01475 0.00463 -0.0170 1.0000 1.0000
2.750 0.2727 0.01529 0.00525 -0.0176 1.0000 1.0000
3.000 0.2933 0.01596 0.00598 -0.0186 1.0000 1.0000
3.250 0.3471 0.01674 0.00699 -0.0258 0.9778 1.0000
3.500 0.4460 0.01695 0.00774 -0.0385 0.9150 1.0000
3.750 0.4913 0.01703 0.00802 -0.0389 0.8523 1.0000
4.000 0.5134 0.01732 0.00832 -0.0347 0.7936 1.0000
4.250 0.5296 0.01781 0.00870 -0.0296 0.7350 1.0000
4.500 0.5456 0.01844 0.00921 -0.0249 0.6686 1.0000
4.750 0.5620 0.01867 0.00936 -0.0204 0.5871 1.0000
5.000 0.5791 0.01912 0.00932 -0.0162 0.4850 1.0000
5.250 0.5990 0.02037 0.00992 -0.0135 0.3825 1.0000
5.500 0.6226 0.02200 0.01113 -0.0122 0.3129 1.0000
5.750 0.6468 0.02365 0.01245 -0.0112 0.2663 1.0000
6.000 0.6727 0.02551 0.01444 -0.0105 0.2328 1.0000
6.250 0.6979 0.02741 0.01638 -0.0098 0.2056 1.0000
6.500 0.7242 0.02979 0.01895 -0.0092 0.1878 1.0000
6.750 0.7484 0.03205 0.02134 -0.0087 0.1681 1.0000
7.000 0.7736 0.03504 0.02463 -0.0082 0.1574 1.0000
7.250 0.7970 0.03891 0.02933 -0.0082 0.1494 1.0000
7.500 0.8179 0.04230 0.03317 -0.0081 0.1383 1.0000
7.750 0.8366 0.04747 0.03906 -0.0088 0.1365 1.0000
8.000 0.8514 0.05367 0.04590 -0.0103 0.1383 1.0000
8.250 0.8641 0.05998 0.05261 -0.0120 0.1411 1.0000
8.500 0.8744 0.06620 0.05911 -0.0138 0.1423 1.0000
8.750 0.6485 0.08894 0.08232 -0.0522 0.3711 1.0000
9.000 0.6549 0.09374 0.08722 -0.0523 0.3652 1.0000
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Polar data table (+)
Polar graphs
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