AG04 (ag04-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG04 (ag04-il) Reynolds number: 500,000 Max Cl/Cd: 72.78 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag04-il-500000-n5.txt Download as CSV file: xf-ag04-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG04
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4926 0.14556 0.14336 0.0209 1.0000 0.0079
-12.250 -0.4901 0.14234 0.14015 0.0200 1.0000 0.0079
-12.000 -0.6370 0.15241 0.15009 0.0391 1.0000 0.0078
-11.750 -0.6320 0.14849 0.14615 0.0376 1.0000 0.0078
-9.000 -0.5998 0.10102 0.09881 0.0203 1.0000 0.0047
-8.750 -0.5987 0.09665 0.09446 0.0181 1.0000 0.0046
-8.500 -0.5979 0.09216 0.08999 0.0157 1.0000 0.0046
-8.250 -0.5976 0.08753 0.08538 0.0129 1.0000 0.0045
-8.000 -0.5977 0.08268 0.08057 0.0095 1.0000 0.0045
-7.750 -0.5948 0.07690 0.07481 0.0036 1.0000 0.0044
-7.500 -0.5870 0.06970 0.06760 -0.0050 1.0000 0.0044
-7.250 -0.5752 0.06048 0.05833 -0.0157 1.0000 0.0043
-7.000 -0.5614 0.04606 0.04365 -0.0287 1.0000 0.0043
-6.750 -0.5569 0.02295 0.01894 -0.0369 1.0000 0.0044
-6.500 -0.5335 0.01998 0.01544 -0.0370 1.0000 0.0046
-6.250 -0.5084 0.01825 0.01336 -0.0369 1.0000 0.0048
-6.000 -0.4841 0.01586 0.01056 -0.0368 1.0000 0.0051
-5.750 -0.4584 0.01473 0.00925 -0.0366 1.0000 0.0054
-5.500 -0.4320 0.01415 0.00859 -0.0364 1.0000 0.0058
-5.250 -0.4056 0.01360 0.00796 -0.0362 1.0000 0.0065
-5.000 -0.3792 0.01280 0.00702 -0.0359 1.0000 0.0070
-4.750 -0.3529 0.01191 0.00597 -0.0356 1.0000 0.0072
-4.500 -0.3265 0.01119 0.00514 -0.0352 1.0000 0.0075
-4.250 -0.3000 0.01062 0.00448 -0.0348 1.0000 0.0079
-4.000 -0.2736 0.00991 0.00368 -0.0345 1.0000 0.0093
-3.750 -0.2472 0.00954 0.00326 -0.0341 1.0000 0.0110
-3.500 -0.2209 0.00917 0.00285 -0.0337 1.0000 0.0139
-3.250 -0.1867 0.00880 0.00249 -0.0351 0.9920 0.0228
-3.000 -0.1520 0.00847 0.00221 -0.0366 0.9807 0.0378
-2.750 -0.1177 0.00816 0.00199 -0.0380 0.9662 0.0614
-2.500 -0.0845 0.00790 0.00180 -0.0391 0.9474 0.0865
-2.250 -0.0545 0.00769 0.00162 -0.0394 0.9240 0.1138
-2.000 -0.0277 0.00752 0.00148 -0.0389 0.8966 0.1447
-1.750 -0.0019 0.00739 0.00136 -0.0382 0.8666 0.1780
-1.500 0.0239 0.00727 0.00125 -0.0376 0.8346 0.2176
-1.250 0.0499 0.00718 0.00115 -0.0370 0.8018 0.2618
-1.000 0.0763 0.00709 0.00108 -0.0366 0.7692 0.3126
-0.750 0.1028 0.00700 0.00102 -0.0363 0.7369 0.3687
0.000 0.1825 0.00658 0.00096 -0.0354 0.6446 0.6044
0.250 0.2071 0.00624 0.00097 -0.0346 0.6145 0.7405
0.500 0.2376 0.00581 0.00096 -0.0346 0.5830 1.0000
1.000 0.2922 0.00614 0.00098 -0.0342 0.5205 1.0000
1.250 0.3195 0.00632 0.00102 -0.0340 0.4891 1.0000
1.500 0.3469 0.00651 0.00106 -0.0339 0.4583 1.0000
2.000 0.4015 0.00691 0.00120 -0.0336 0.3984 1.0000
2.250 0.4289 0.00711 0.00129 -0.0335 0.3703 1.0000
2.500 0.4562 0.00733 0.00139 -0.0334 0.3433 1.0000
2.750 0.4835 0.00755 0.00152 -0.0333 0.3168 1.0000
3.000 0.5108 0.00777 0.00165 -0.0332 0.2911 1.0000
3.250 0.5380 0.00801 0.00179 -0.0331 0.2661 1.0000
3.500 0.5652 0.00826 0.00195 -0.0330 0.2422 1.0000
3.750 0.5923 0.00852 0.00214 -0.0328 0.2193 1.0000
4.000 0.6193 0.00878 0.00233 -0.0327 0.1967 1.0000
4.250 0.6464 0.00906 0.00254 -0.0326 0.1766 1.0000
4.500 0.6732 0.00936 0.00276 -0.0325 0.1553 1.0000
4.750 0.7001 0.00966 0.00303 -0.0323 0.1361 1.0000
5.000 0.7267 0.01000 0.00330 -0.0322 0.1163 1.0000
5.250 0.7533 0.01035 0.00360 -0.0320 0.0988 1.0000
5.500 0.7798 0.01072 0.00392 -0.0319 0.0812 1.0000
5.750 0.8061 0.01113 0.00427 -0.0317 0.0657 1.0000
6.000 0.8322 0.01156 0.00468 -0.0315 0.0520 1.0000
6.250 0.8583 0.01198 0.00509 -0.0313 0.0418 1.0000
6.500 0.8843 0.01242 0.00553 -0.0310 0.0328 1.0000
6.750 0.9101 0.01290 0.00602 -0.0308 0.0259 1.0000
7.000 0.9356 0.01343 0.00654 -0.0305 0.0198 1.0000
7.250 0.9612 0.01391 0.00709 -0.0302 0.0163 1.0000
7.500 0.9862 0.01453 0.00775 -0.0299 0.0125 1.0000
7.750 1.0113 0.01508 0.00838 -0.0296 0.0103 1.0000
8.000 1.0360 0.01570 0.00905 -0.0292 0.0086 1.0000
8.250 1.0596 0.01658 0.01004 -0.0287 0.0071 1.0000
8.500 1.0837 0.01729 0.01087 -0.0283 0.0064 1.0000
8.750 1.1072 0.01809 0.01179 -0.0278 0.0057 1.0000
9.000 1.1301 0.01896 0.01277 -0.0273 0.0051 1.0000
9.250 1.1512 0.02016 0.01413 -0.0266 0.0045 1.0000
9.500 1.1721 0.02133 0.01546 -0.0259 0.0041 1.0000
9.750 1.1938 0.02226 0.01654 -0.0253 0.0038 1.0000
10.000 1.2143 0.02334 0.01778 -0.0246 0.0035 1.0000
10.250 1.2333 0.02463 0.01924 -0.0239 0.0033 1.0000
10.500 1.2514 0.02598 0.02077 -0.0230 0.0031 1.0000
10.750 1.2683 0.02740 0.02236 -0.0222 0.0029 1.0000
11.000 1.2838 0.02893 0.02407 -0.0213 0.0028 1.0000
11.250 1.2969 0.03067 0.02600 -0.0202 0.0027 1.0000
11.500 1.3056 0.03281 0.02835 -0.0190 0.0026 1.0000
11.750 1.3076 0.03555 0.03134 -0.0175 0.0025 1.0000
12.000 1.2983 0.03883 0.03493 -0.0154 0.0024 1.0000
12.250 1.2871 0.04235 0.03866 -0.0147 0.0023 1.0000
12.500 1.2769 0.04668 0.04322 -0.0163 0.0023 1.0000
12.750 1.2646 0.05259 0.04935 -0.0205 0.0023 1.0000
13.000 1.2490 0.06033 0.05730 -0.0266 0.0023 1.0000
13.250 1.2282 0.06976 0.06692 -0.0336 0.0023 1.0000
13.750 1.1905 0.08739 0.08478 -0.0442 0.0024 1.0000
14.000 1.1701 0.09622 0.09370 -0.0488 0.0025 1.0000
14.250 1.1478 0.10544 0.10302 -0.0534 0.0025 1.0000
14.500 1.1209 0.11577 0.11345 -0.0584 0.0026 1.0000
14.750 1.0904 0.12729 0.12508 -0.0639 0.0027 1.0000
15.000 1.0447 0.14402 0.14195 -0.0720 0.0029 1.0000
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Polar data table (+)
Polar graphs
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