AG11 (ag11-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG11 (ag11-il) Reynolds number: 50,000 Max Cl/Cd: 34.61 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag11-il-50000-n5.txt Download as CSV file: xf-ag11-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5319 0.11433 0.10750 0.0119 1.0000 0.0807
-8.250 -0.5349 0.11233 0.10560 0.0071 1.0000 0.0817
-8.000 -0.5346 0.10984 0.10318 0.0006 1.0000 0.0822
-7.750 -0.5173 0.10324 0.09661 0.0072 1.0000 0.0850
-7.500 -0.5094 0.09965 0.09305 0.0068 1.0000 0.0887
-7.250 -0.5042 0.09641 0.08986 0.0030 1.0000 0.0932
-7.000 -0.4980 0.09384 0.08728 -0.0091 1.0000 0.0963
-6.750 -0.4876 0.08865 0.08217 -0.0030 1.0000 0.1002
-6.500 -0.4767 0.08514 0.07867 -0.0058 1.0000 0.1071
-6.000 -0.4528 0.07750 0.07107 -0.0110 1.0000 0.1201
-5.750 -0.4392 0.07357 0.06712 -0.0145 1.0000 0.1286
-5.500 -0.4233 0.06996 0.06345 -0.0186 1.0000 0.1410
-5.250 -0.4069 0.06648 0.05991 -0.0212 1.0000 0.1547
-5.000 -0.3916 0.06272 0.05621 -0.0202 1.0000 0.1616
-4.750 -0.3738 0.05926 0.05271 -0.0220 1.0000 0.1773
-4.500 -0.3190 0.05116 0.04378 -0.0309 1.0000 0.0625
-4.250 -0.2907 0.04694 0.03918 -0.0327 1.0000 0.0508
-4.000 -0.2656 0.04326 0.03521 -0.0338 1.0000 0.0469
-3.750 -0.2329 0.03979 0.03097 -0.0348 1.0000 0.0418
-3.500 -0.2075 0.03696 0.02783 -0.0349 1.0000 0.0405
-3.250 -0.1820 0.03411 0.02470 -0.0350 1.0000 0.0399
-3.000 -0.1556 0.03158 0.02182 -0.0348 1.0000 0.0394
-2.750 -0.1286 0.02941 0.01924 -0.0344 1.0000 0.0400
-2.500 -0.1016 0.02751 0.01694 -0.0339 1.0000 0.0417
-2.250 -0.0766 0.02555 0.01483 -0.0335 1.0000 0.0445
-2.000 -0.0506 0.02398 0.01304 -0.0327 1.0000 0.0460
-1.750 -0.0247 0.02257 0.01143 -0.0317 1.0000 0.0477
-1.500 0.0007 0.02143 0.01008 -0.0306 1.0000 0.0514
-1.250 0.0264 0.02038 0.00891 -0.0298 1.0000 0.0587
-1.000 0.0519 0.01951 0.00785 -0.0291 1.0000 0.0666
-0.750 0.0775 0.01864 0.00701 -0.0287 1.0000 0.0863
-0.500 0.1031 0.01589 0.00623 -0.0292 1.0000 0.4762
-0.250 0.1251 0.01477 0.00573 -0.0267 1.0000 1.0000
0.000 0.1480 0.01494 0.00557 -0.0260 1.0000 1.0000
0.250 0.1705 0.01516 0.00553 -0.0255 1.0000 1.0000
0.500 0.2018 0.01541 0.00558 -0.0268 0.9928 1.0000
0.750 0.2531 0.01563 0.00560 -0.0318 0.9699 1.0000
1.000 0.3020 0.01579 0.00561 -0.0360 0.9445 1.0000
1.250 0.3463 0.01590 0.00564 -0.0390 0.9159 1.0000
1.500 0.3861 0.01599 0.00567 -0.0408 0.8840 1.0000
1.750 0.4204 0.01609 0.00571 -0.0413 0.8483 1.0000
2.000 0.4513 0.01621 0.00575 -0.0410 0.8112 1.0000
2.250 0.4788 0.01636 0.00581 -0.0399 0.7724 1.0000
2.500 0.5041 0.01657 0.00593 -0.0384 0.7320 1.0000
2.750 0.5284 0.01683 0.00605 -0.0368 0.6908 1.0000
3.000 0.5523 0.01714 0.00621 -0.0352 0.6487 1.0000
3.250 0.5760 0.01750 0.00642 -0.0337 0.6059 1.0000
3.500 0.5996 0.01791 0.00667 -0.0324 0.5628 1.0000
3.750 0.6232 0.01837 0.00703 -0.0311 0.5198 1.0000
4.000 0.6468 0.01888 0.00738 -0.0300 0.4774 1.0000
4.250 0.6704 0.01945 0.00780 -0.0290 0.4362 1.0000
4.500 0.6940 0.02006 0.00828 -0.0281 0.3968 1.0000
4.750 0.7181 0.02075 0.00882 -0.0275 0.3594 1.0000
5.000 0.7423 0.02147 0.00955 -0.0269 0.3228 1.0000
5.250 0.7661 0.02227 0.01024 -0.0263 0.2898 1.0000
5.500 0.7899 0.02312 0.01103 -0.0258 0.2597 1.0000
5.750 0.8134 0.02403 0.01189 -0.0253 0.2323 1.0000
6.000 0.8369 0.02500 0.01293 -0.0248 0.2074 1.0000
6.250 0.8604 0.02607 0.01403 -0.0242 0.1870 1.0000
6.500 0.8836 0.02721 0.01523 -0.0237 0.1691 1.0000
6.750 0.9063 0.02837 0.01644 -0.0231 0.1533 1.0000
7.000 0.9296 0.02974 0.01800 -0.0225 0.1416 1.0000
7.250 0.9524 0.03121 0.01962 -0.0218 0.1315 1.0000
7.500 0.9743 0.03260 0.02108 -0.0213 0.1216 1.0000
7.750 0.9963 0.03422 0.02297 -0.0206 0.1130 1.0000
8.000 1.0182 0.03622 0.02519 -0.0200 0.1075 1.0000
8.250 1.0387 0.03830 0.02769 -0.0193 0.1011 1.0000
8.500 1.0579 0.04021 0.02978 -0.0187 0.0950 1.0000
8.750 1.0748 0.04285 0.03294 -0.0180 0.0896 1.0000
9.000 1.0920 0.04537 0.03573 -0.0173 0.0861 1.0000
9.250 1.1062 0.04849 0.03916 -0.0166 0.0832 1.0000
9.500 1.1107 0.05272 0.04411 -0.0158 0.0797 1.0000
9.750 1.1166 0.05601 0.04779 -0.0152 0.0758 1.0000
10.000 1.1263 0.05860 0.05059 -0.0145 0.0728 1.0000
10.250 1.1276 0.06267 0.05491 -0.0140 0.0714 1.0000
10.500 1.1117 0.06826 0.06095 -0.0140 0.0709 1.0000
10.750 1.0898 0.07385 0.06682 -0.0146 0.0708 1.0000
11.000 1.0642 0.08003 0.07316 -0.0169 0.0709 1.0000
11.250 1.0376 0.08786 0.08102 -0.0222 0.0713 1.0000
11.500 1.0116 0.09740 0.09058 -0.0292 0.0716 1.0000
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Polar data table (+)
Polar graphs
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