AG12 (ag12-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG12 (ag12-il) Reynolds number: 500,000 Max Cl/Cd: 79.62 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag12-il-500000.txt Download as CSV file: xf-ag12-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG12
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 0.2509 0.00481 0.00107 -0.0467 0.8066 1.0000
0.500 0.2771 0.00498 0.00105 -0.0460 0.7672 1.0000
0.750 0.3036 0.00517 0.00104 -0.0455 0.7285 1.0000
1.000 0.3303 0.00537 0.00105 -0.0451 0.6901 1.0000
1.250 0.3572 0.00557 0.00108 -0.0447 0.6523 1.0000
1.500 0.3843 0.00577 0.00112 -0.0444 0.6151 1.0000
1.750 0.4115 0.00598 0.00118 -0.0441 0.5789 1.0000
2.000 0.4387 0.00620 0.00125 -0.0439 0.5434 1.0000
2.250 0.4660 0.00642 0.00133 -0.0437 0.5089 1.0000
2.500 0.4932 0.00665 0.00143 -0.0436 0.4750 1.0000
2.750 0.5205 0.00688 0.00153 -0.0434 0.4410 1.0000
3.000 0.5477 0.00714 0.00168 -0.0432 0.4076 1.0000
3.250 0.5749 0.00739 0.00182 -0.0431 0.3753 1.0000
3.500 0.6020 0.00767 0.00198 -0.0430 0.3423 1.0000
3.750 0.6291 0.00795 0.00216 -0.0428 0.3111 1.0000
4.000 0.6561 0.00826 0.00237 -0.0427 0.2786 1.0000
4.250 0.6831 0.00858 0.00259 -0.0426 0.2484 1.0000
4.500 0.7099 0.00894 0.00284 -0.0424 0.2160 1.0000
4.750 0.7366 0.00931 0.00311 -0.0423 0.1877 1.0000
5.000 0.7632 0.00971 0.00340 -0.0421 0.1587 1.0000
5.250 0.7896 0.01013 0.00376 -0.0420 0.1323 1.0000
5.500 0.8159 0.01059 0.00412 -0.0418 0.1069 1.0000
5.750 0.8422 0.01104 0.00452 -0.0416 0.0859 1.0000
6.000 0.8682 0.01156 0.00497 -0.0413 0.0669 1.0000
6.250 0.8941 0.01209 0.00546 -0.0411 0.0510 1.0000
6.500 0.9198 0.01269 0.00601 -0.0408 0.0374 1.0000
6.750 0.9452 0.01335 0.00672 -0.0405 0.0273 1.0000
7.000 0.9703 0.01410 0.00751 -0.0400 0.0196 1.0000
7.250 0.9934 0.01541 0.00893 -0.0393 0.0140 1.0000
7.500 1.0182 0.01620 0.00983 -0.0388 0.0119 1.0000
7.750 1.0418 0.01721 0.01095 -0.0382 0.0102 1.0000
8.000 1.0604 0.01955 0.01352 -0.0370 0.0089 1.0000
8.250 1.0768 0.02265 0.01695 -0.0355 0.0085 1.0000
8.500 1.0991 0.02388 0.01837 -0.0348 0.0082 1.0000
8.750 1.1210 0.02504 0.01976 -0.0341 0.0077 1.0000
9.000 1.1412 0.02657 0.02149 -0.0333 0.0071 1.0000
9.250 1.1575 0.02900 0.02422 -0.0322 0.0069 1.0000
9.500 1.1716 0.03169 0.02723 -0.0311 0.0067 1.0000
9.750 1.1826 0.03467 0.03054 -0.0299 0.0065 1.0000
10.000 1.1899 0.03790 0.03410 -0.0287 0.0063 1.0000
10.250 1.1927 0.04138 0.03790 -0.0275 0.0061 1.0000
10.500 1.1882 0.04537 0.04219 -0.0264 0.0060 1.0000
10.750 1.1739 0.04948 0.04658 -0.0252 0.0060 1.0000
11.000 1.1506 0.05529 0.05267 -0.0273 0.0061 1.0000
11.250 1.1258 0.06410 0.06174 -0.0348 0.0063 1.0000
11.500 1.1008 0.07554 0.07339 -0.0450 0.0065 1.0000
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Polar data table (+)
Polar graphs
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