AG16 (ag16-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG16 (ag16-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.39 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag16-il-1000000-n5.txt Download as CSV file: xf-ag16-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG16
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6749 0.02525 0.02249 -0.0476 1.0000 0.0026
-8.000 -0.6549 0.02065 0.01730 -0.0491 1.0000 0.0026
-7.750 -0.6315 0.01794 0.01418 -0.0496 1.0000 0.0026
-7.500 -0.6066 0.01608 0.01202 -0.0498 1.0000 0.0027
-7.250 -0.5810 0.01471 0.01041 -0.0499 1.0000 0.0028
-7.000 -0.5548 0.01367 0.00919 -0.0498 1.0000 0.0029
-6.750 -0.5283 0.01289 0.00825 -0.0498 1.0000 0.0030
-6.500 -0.5017 0.01207 0.00730 -0.0497 1.0000 0.0031
-6.250 -0.4753 0.01096 0.00602 -0.0496 1.0000 0.0036
-6.000 -0.4484 0.01050 0.00551 -0.0495 1.0000 0.0039
-5.750 -0.4216 0.01010 0.00506 -0.0493 1.0000 0.0042
-5.500 -0.3948 0.00970 0.00460 -0.0491 1.0000 0.0045
-5.250 -0.3679 0.00931 0.00415 -0.0489 0.9999 0.0048
-5.000 -0.3347 0.00891 0.00367 -0.0501 0.9944 0.0051
-4.750 -0.3020 0.00858 0.00329 -0.0511 0.9865 0.0054
-4.500 -0.2688 0.00818 0.00284 -0.0523 0.9767 0.0065
-4.250 -0.2362 0.00789 0.00252 -0.0532 0.9632 0.0080
-4.000 -0.2062 0.00768 0.00225 -0.0535 0.9444 0.0093
-3.750 -0.1789 0.00746 0.00196 -0.0532 0.9212 0.0133
-3.500 -0.1526 0.00732 0.00176 -0.0526 0.8964 0.0192
-3.250 -0.1262 0.00716 0.00156 -0.0521 0.8696 0.0321
-3.000 -0.0995 0.00703 0.00139 -0.0518 0.8419 0.0499
-2.750 -0.0724 0.00690 0.00123 -0.0515 0.8140 0.0717
-2.500 -0.0451 0.00677 0.00109 -0.0513 0.7854 0.1001
-2.250 -0.0177 0.00663 0.00097 -0.0512 0.7568 0.1379
-2.000 0.0099 0.00654 0.00088 -0.0511 0.7293 0.1697
-1.750 0.0376 0.00648 0.00080 -0.0510 0.7016 0.2012
-1.500 0.0654 0.00643 0.00074 -0.0510 0.6742 0.2320
-1.250 0.0933 0.00643 0.00069 -0.0509 0.6476 0.2541
-1.000 0.1212 0.00643 0.00066 -0.0509 0.6214 0.2792
-0.750 0.1491 0.00639 0.00064 -0.0509 0.5955 0.3172
-0.500 0.1770 0.00638 0.00062 -0.0508 0.5704 0.3475
-0.250 0.2050 0.00639 0.00062 -0.0508 0.5444 0.3782
0.000 0.2329 0.00640 0.00063 -0.0508 0.5201 0.4098
0.250 0.2609 0.00642 0.00065 -0.0508 0.4960 0.4407
0.500 0.2888 0.00645 0.00068 -0.0508 0.4712 0.4739
0.750 0.3167 0.00648 0.00072 -0.0508 0.4462 0.5072
1.000 0.3445 0.00651 0.00077 -0.0508 0.4226 0.5436
1.250 0.3724 0.00655 0.00082 -0.0508 0.3996 0.5828
1.500 0.4001 0.00658 0.00090 -0.0507 0.3757 0.6269
1.750 0.4276 0.00658 0.00098 -0.0507 0.3523 0.6805
2.000 0.4547 0.00654 0.00107 -0.0505 0.3297 0.7526
2.250 0.4759 0.00623 0.00116 -0.0488 0.3085 0.9154
2.500 0.5060 0.00632 0.00123 -0.0492 0.2852 1.0000
2.750 0.5337 0.00652 0.00135 -0.0491 0.2622 1.0000
3.000 0.5614 0.00674 0.00147 -0.0491 0.2384 1.0000
3.250 0.5890 0.00697 0.00160 -0.0490 0.2150 1.0000
3.500 0.6166 0.00718 0.00173 -0.0490 0.1967 1.0000
3.750 0.6440 0.00743 0.00190 -0.0489 0.1743 1.0000
4.000 0.6714 0.00769 0.00208 -0.0489 0.1532 1.0000
4.250 0.6987 0.00796 0.00227 -0.0488 0.1333 1.0000
4.750 0.7531 0.00852 0.00270 -0.0486 0.0975 1.0000
5.000 0.7799 0.00887 0.00296 -0.0485 0.0772 1.0000
5.250 0.8069 0.00918 0.00321 -0.0483 0.0638 1.0000
5.500 0.8337 0.00950 0.00349 -0.0482 0.0514 1.0000
5.750 0.8603 0.00989 0.00381 -0.0480 0.0372 1.0000
6.000 0.8866 0.01031 0.00416 -0.0479 0.0254 1.0000
6.250 0.9132 0.01067 0.00452 -0.0477 0.0187 1.0000
6.500 0.9395 0.01106 0.00489 -0.0475 0.0133 1.0000
6.750 0.9659 0.01143 0.00527 -0.0473 0.0104 1.0000
7.000 0.9920 0.01184 0.00569 -0.0470 0.0076 1.0000
7.250 1.0181 0.01226 0.00613 -0.0468 0.0058 1.0000
7.500 1.0438 0.01275 0.00665 -0.0465 0.0044 1.0000
7.750 1.0695 0.01321 0.00717 -0.0462 0.0037 1.0000
8.000 1.0949 0.01372 0.00774 -0.0459 0.0032 1.0000
8.250 1.1197 0.01436 0.00845 -0.0455 0.0026 1.0000
8.500 1.1442 0.01502 0.00920 -0.0451 0.0024 1.0000
8.750 1.1688 0.01559 0.00985 -0.0447 0.0023 1.0000
9.000 1.1931 0.01623 0.01058 -0.0443 0.0022 1.0000
9.250 1.2168 0.01693 0.01137 -0.0438 0.0021 1.0000
9.500 1.2401 0.01768 0.01222 -0.0433 0.0020 1.0000
9.750 1.2629 0.01848 0.01313 -0.0427 0.0019 1.0000
10.000 1.2852 0.01933 0.01411 -0.0421 0.0018 1.0000
10.250 1.3069 0.02022 0.01511 -0.0415 0.0017 1.0000
10.500 1.3280 0.02116 0.01617 -0.0408 0.0017 1.0000
10.750 1.3485 0.02213 0.01726 -0.0401 0.0016 1.0000
11.000 1.3683 0.02316 0.01840 -0.0393 0.0015 1.0000
11.250 1.3872 0.02425 0.01961 -0.0385 0.0015 1.0000
11.500 1.4049 0.02543 0.02092 -0.0376 0.0014 1.0000
11.750 1.4209 0.02676 0.02239 -0.0366 0.0013 1.0000
12.000 1.4339 0.02837 0.02416 -0.0353 0.0013 1.0000
12.250 1.4417 0.03046 0.02645 -0.0337 0.0012 1.0000
12.500 1.4397 0.03338 0.02966 -0.0315 0.0011 1.0000
12.750 1.4230 0.03682 0.03339 -0.0284 0.0011 1.0000
13.000 1.4174 0.03956 0.03628 -0.0273 0.0011 1.0000
13.250 1.4103 0.04312 0.04001 -0.0278 0.0010 1.0000
13.500 1.3985 0.04822 0.04530 -0.0304 0.0010 1.0000
13.750 1.3851 0.05463 0.05189 -0.0347 0.0010 1.0000
14.000 1.3639 0.06335 0.06081 -0.0409 0.0010 1.0000
14.250 1.3348 0.07409 0.07173 -0.0479 0.0011 1.0000
14.500 1.2995 0.08604 0.08383 -0.0548 0.0011 1.0000
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Polar data table (+)
Polar graphs
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