AG09 (ag09-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG09 (ag09-il) Reynolds number: 500,000 Max Cl/Cd: 74.35 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag09-il-500000.txt Download as CSV file: xf-ag09-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG09
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.250 0.2143 0.00454 0.00113 -0.0349 0.8921 1.0000
0.500 0.2383 0.00468 0.00108 -0.0335 0.8465 1.0000
0.750 0.2631 0.00487 0.00105 -0.0325 0.7998 1.0000
1.000 0.2889 0.00508 0.00104 -0.0317 0.7514 1.0000
1.250 0.3150 0.00532 0.00104 -0.0311 0.7008 1.0000
1.500 0.3415 0.00556 0.00106 -0.0306 0.6486 1.0000
1.750 0.3683 0.00583 0.00111 -0.0303 0.5963 1.0000
2.000 0.3952 0.00611 0.00117 -0.0300 0.5435 1.0000
2.250 0.4222 0.00640 0.00125 -0.0298 0.4932 1.0000
2.500 0.4493 0.00669 0.00135 -0.0297 0.4471 1.0000
2.750 0.4765 0.00697 0.00148 -0.0295 0.4053 1.0000
3.000 0.5037 0.00725 0.00162 -0.0294 0.3673 1.0000
3.250 0.5310 0.00753 0.00176 -0.0293 0.3325 1.0000
3.500 0.5582 0.00780 0.00192 -0.0292 0.3000 1.0000
3.750 0.5855 0.00809 0.00212 -0.0291 0.2700 1.0000
4.000 0.6126 0.00838 0.00231 -0.0290 0.2414 1.0000
4.250 0.6397 0.00868 0.00252 -0.0289 0.2143 1.0000
4.500 0.6668 0.00899 0.00275 -0.0288 0.1882 1.0000
4.750 0.6937 0.00933 0.00302 -0.0287 0.1617 1.0000
5.000 0.7205 0.00970 0.00330 -0.0286 0.1348 1.0000
5.250 0.7471 0.01012 0.00362 -0.0285 0.1064 1.0000
5.500 0.7734 0.01064 0.00400 -0.0283 0.0760 1.0000
5.750 0.7993 0.01128 0.00450 -0.0282 0.0464 1.0000
6.000 0.8249 0.01209 0.00525 -0.0278 0.0263 1.0000
6.250 0.8506 0.01292 0.00613 -0.0274 0.0189 1.0000
6.500 0.8757 0.01388 0.00715 -0.0270 0.0153 1.0000
6.750 0.8999 0.01510 0.00854 -0.0264 0.0138 1.0000
7.000 0.9245 0.01611 0.00968 -0.0258 0.0128 1.0000
7.250 0.9483 0.01734 0.01107 -0.0252 0.0121 1.0000
7.500 0.9716 0.01873 0.01263 -0.0245 0.0117 1.0000
7.750 0.9950 0.01994 0.01396 -0.0239 0.0110 1.0000
8.000 1.0174 0.02127 0.01539 -0.0234 0.0103 1.0000
8.250 1.0370 0.02367 0.01804 -0.0225 0.0099 1.0000
8.500 1.0548 0.02667 0.02137 -0.0215 0.0098 1.0000
8.750 1.0697 0.03026 0.02535 -0.0205 0.0097 1.0000
9.000 1.0815 0.03416 0.02971 -0.0194 0.0097 1.0000
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Polar data table (+)
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