AG13 (ag13-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG13 (ag13-il) Reynolds number: 100,000 Max Cl/Cd: 48.2 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag13-il-100000.txt Download as CSV file: xf-ag13-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG13
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5729 0.12194 0.11704 0.0189 1.0000 0.0622
-9.000 -0.5754 0.11975 0.11491 0.0139 1.0000 0.0628
-8.750 -0.5768 0.11713 0.11237 0.0090 1.0000 0.0630
-8.500 -0.5531 0.10955 0.10473 0.0174 1.0000 0.0683
-8.250 -0.5483 0.10622 0.10144 0.0157 1.0000 0.0719
-8.000 -0.5483 0.10336 0.09864 0.0114 1.0000 0.0748
-7.750 -0.5499 0.10072 0.09610 0.0027 1.0000 0.0759
-7.500 -0.5418 0.09531 0.09072 0.0058 1.0000 0.0781
-7.250 -0.5306 0.09170 0.08712 0.0075 1.0000 0.0818
-7.000 -0.5220 0.08792 0.08337 0.0032 1.0000 0.0862
-6.750 -0.5063 0.08218 0.07759 -0.0165 1.0000 0.0901
-6.500 -0.5000 0.07878 0.07429 -0.0070 1.0000 0.0929
-6.250 -0.4858 0.07500 0.07050 -0.0094 1.0000 0.0984
-6.000 -0.4658 0.06904 0.06447 -0.0203 1.0000 0.1049
-5.750 -0.4521 0.06588 0.06135 -0.0187 1.0000 0.1100
-5.500 -0.4297 0.06058 0.05594 -0.0261 1.0000 0.1195
-5.250 -0.4057 0.05598 0.05117 -0.0319 1.0000 0.1318
-5.000 -0.3883 0.05287 0.04807 -0.0308 1.0000 0.1387
-4.750 -0.3652 0.04893 0.04402 -0.0336 1.0000 0.1514
-4.500 -0.3386 0.04498 0.03983 -0.0379 1.0000 0.1730
-4.250 -0.2774 0.02975 0.02273 -0.0473 1.0000 0.0594
-4.000 -0.2483 0.02614 0.01858 -0.0478 1.0000 0.0576
-3.750 -0.2190 0.02358 0.01544 -0.0478 1.0000 0.0605
-3.500 -0.1898 0.02106 0.01242 -0.0475 1.0000 0.0611
-3.250 -0.1610 0.01895 0.00991 -0.0468 1.0000 0.0637
-3.000 -0.1340 0.01738 0.00827 -0.0464 1.0000 0.0753
-2.750 -0.1072 0.01565 0.00664 -0.0459 1.0000 0.0927
-2.500 -0.0803 0.01422 0.00542 -0.0455 1.0000 0.1415
-2.250 -0.0541 0.01243 0.00459 -0.0455 1.0000 0.3099
-2.000 -0.0312 0.01122 0.00435 -0.0443 1.0000 0.5479
-1.750 -0.0118 0.00974 0.00398 -0.0406 1.0000 0.9985
-1.500 0.0158 0.00975 0.00362 -0.0407 1.0000 1.0000
-1.250 0.0427 0.00977 0.00333 -0.0405 1.0000 1.0000
-1.000 0.0691 0.00980 0.00316 -0.0403 1.0000 1.0000
-0.750 0.0954 0.00985 0.00304 -0.0401 1.0000 1.0000
-0.500 0.1214 0.00992 0.00298 -0.0399 1.0000 1.0000
-0.250 0.1472 0.01002 0.00296 -0.0398 1.0000 1.0000
0.000 0.1728 0.01014 0.00298 -0.0396 1.0000 1.0000
0.250 0.1982 0.01029 0.00308 -0.0395 1.0000 1.0000
0.500 0.2234 0.01048 0.00325 -0.0396 1.0000 1.0000
0.750 0.2483 0.01074 0.00350 -0.0397 1.0000 1.0000
1.000 0.2725 0.01109 0.00385 -0.0401 1.0000 1.0000
1.250 0.3317 0.01129 0.00410 -0.0469 0.9772 1.0000
1.500 0.3907 0.01129 0.00418 -0.0528 0.9492 1.0000
1.750 0.4378 0.01122 0.00421 -0.0558 0.9149 1.0000
2.000 0.4724 0.01120 0.00419 -0.0559 0.8736 1.0000
2.250 0.4991 0.01128 0.00421 -0.0543 0.8281 1.0000
2.500 0.5229 0.01145 0.00427 -0.0522 0.7810 1.0000
2.750 0.5460 0.01171 0.00438 -0.0502 0.7335 1.0000
3.000 0.5693 0.01203 0.00459 -0.0484 0.6847 1.0000
3.250 0.5930 0.01241 0.00479 -0.0468 0.6364 1.0000
3.500 0.6169 0.01283 0.00504 -0.0454 0.5873 1.0000
3.750 0.6410 0.01330 0.00533 -0.0442 0.5378 1.0000
4.000 0.6652 0.01382 0.00565 -0.0431 0.4892 1.0000
4.250 0.6896 0.01437 0.00610 -0.0422 0.4393 1.0000
4.500 0.7138 0.01501 0.00654 -0.0413 0.3922 1.0000
4.750 0.7382 0.01568 0.00708 -0.0406 0.3441 1.0000
5.000 0.7623 0.01646 0.00768 -0.0399 0.2994 1.0000
5.250 0.7864 0.01734 0.00839 -0.0392 0.2576 1.0000
5.500 0.8105 0.01830 0.00931 -0.0386 0.2191 1.0000
5.750 0.8343 0.01941 0.01028 -0.0380 0.1858 1.0000
6.000 0.8583 0.02060 0.01145 -0.0373 0.1562 1.0000
6.250 0.8820 0.02192 0.01273 -0.0366 0.1308 1.0000
6.500 0.9055 0.02344 0.01420 -0.0359 0.1097 1.0000
6.750 0.9288 0.02509 0.01600 -0.0352 0.0903 1.0000
7.000 0.9523 0.02735 0.01849 -0.0342 0.0769 1.0000
7.250 0.9745 0.02940 0.02074 -0.0334 0.0643 1.0000
7.500 0.9957 0.03296 0.02436 -0.0326 0.0573 1.0000
7.750 1.0162 0.03533 0.02744 -0.0313 0.0507 1.0000
8.000 1.0344 0.03850 0.03074 -0.0306 0.0461 1.0000
8.250 1.0459 0.04416 0.03700 -0.0295 0.0449 1.0000
8.500 1.0545 0.04922 0.04273 -0.0284 0.0446 1.0000
8.750 1.0584 0.05503 0.04905 -0.0277 0.0448 1.0000
9.000 1.0581 0.06105 0.05548 -0.0273 0.0451 1.0000
9.250 1.0290 0.06949 0.06494 -0.0292 0.0497 1.0000
9.500 1.0042 0.07675 0.07244 -0.0323 0.0515 1.0000
9.750 0.9805 0.08470 0.08049 -0.0388 0.0528 1.0000
10.000 0.9635 0.09421 0.08999 -0.0467 0.0545 1.0000
10.250 0.9568 0.10088 0.09663 -0.0496 0.0559 1.0000
11.500 0.7576 0.13950 0.13520 -0.0547 0.1209 1.0000
11.750 0.7375 0.14321 0.13885 -0.0585 0.1200 1.0000
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Polar data table (+)
Polar graphs
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