AG16 (ag16-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG16 (ag16-il) Reynolds number: 50,000 Max Cl/Cd: 33.51 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag16-il-50000.txt Download as CSV file: xf-ag16-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5356 0.10901 0.10241 0.0167 1.0000 0.2187
-8.000 -0.5313 0.10539 0.09885 0.0159 1.0000 0.2270
-7.750 -0.5430 0.10417 0.09776 0.0126 1.0000 0.2360
-7.500 -0.5243 0.09897 0.09255 0.0143 1.0000 0.2473
-7.250 -0.5168 0.09505 0.08868 0.0140 1.0000 0.2558
-6.750 -0.5159 0.08906 0.08287 0.0101 1.0000 0.2786
-6.500 -0.5094 0.08559 0.07946 0.0083 1.0000 0.2920
-6.250 -0.5005 0.08187 0.07578 0.0072 1.0000 0.3058
-6.000 -0.4904 0.07802 0.07197 0.0062 1.0000 0.3197
-5.750 -0.4584 0.06258 0.05615 -0.0263 1.0000 0.1796
-5.500 -0.4220 0.04699 0.03929 -0.0447 1.0000 0.1133
-5.250 -0.3990 0.04222 0.03436 -0.0457 1.0000 0.1100
-5.000 -0.3721 0.03733 0.02885 -0.0479 1.0000 0.1099
-4.750 -0.3442 0.03325 0.02407 -0.0492 1.0000 0.1150
-4.500 -0.3170 0.03009 0.02059 -0.0493 1.0000 0.1209
-4.250 -0.2884 0.02707 0.01708 -0.0493 1.0000 0.1312
-4.000 -0.2609 0.02489 0.01464 -0.0490 1.0000 0.1555
-3.750 -0.2342 0.02292 0.01260 -0.0483 1.0000 0.1954
-3.500 -0.2091 0.02122 0.01120 -0.0474 1.0000 0.2628
-3.250 -0.1861 0.01988 0.01033 -0.0458 1.0000 0.3545
-3.000 -0.1642 0.01885 0.00965 -0.0438 1.0000 0.4505
-2.750 -0.1430 0.01800 0.00907 -0.0414 1.0000 0.5411
-2.500 -0.1240 0.01716 0.00849 -0.0385 1.0000 0.6254
-2.250 -0.1082 0.01624 0.00785 -0.0346 1.0000 0.7131
-2.000 -0.0985 0.01517 0.00720 -0.0290 1.0000 0.8214
-1.750 -0.0471 0.01423 0.00595 -0.0347 1.0000 1.0000
-1.500 -0.0165 0.01421 0.00544 -0.0364 1.0000 1.0000
-1.250 0.0109 0.01424 0.00513 -0.0370 1.0000 1.0000
-1.000 0.0371 0.01431 0.00489 -0.0372 1.0000 1.0000
-0.750 0.0626 0.01440 0.00477 -0.0373 1.0000 1.0000
-0.500 0.0876 0.01454 0.00473 -0.0373 1.0000 1.0000
-0.250 0.1121 0.01470 0.00476 -0.0373 1.0000 1.0000
0.000 0.1364 0.01492 0.00484 -0.0373 1.0000 1.0000
0.250 0.1604 0.01518 0.00502 -0.0374 1.0000 1.0000
0.500 0.1840 0.01550 0.00528 -0.0376 1.0000 1.0000
0.750 0.2071 0.01590 0.00564 -0.0378 1.0000 1.0000
1.000 0.2295 0.01638 0.00611 -0.0382 1.0000 1.0000
1.250 0.2511 0.01697 0.00669 -0.0388 1.0000 1.0000
1.500 0.2720 0.01768 0.00742 -0.0396 1.0000 1.0000
1.750 0.2918 0.01854 0.00830 -0.0405 1.0000 1.0000
2.000 0.3542 0.01950 0.00940 -0.0492 0.9764 1.0000
2.250 0.4348 0.02008 0.01024 -0.0597 0.9405 1.0000
2.500 0.5022 0.02026 0.01068 -0.0665 0.9024 1.0000
2.750 0.5515 0.02025 0.01094 -0.0688 0.8639 1.0000
3.000 0.5883 0.02023 0.01105 -0.0681 0.8255 1.0000
3.250 0.6173 0.02024 0.01115 -0.0658 0.7873 1.0000
3.500 0.6417 0.02035 0.01129 -0.0628 0.7482 1.0000
3.750 0.6641 0.02058 0.01159 -0.0596 0.7073 1.0000
4.000 0.6862 0.02090 0.01188 -0.0566 0.6657 1.0000
4.250 0.7082 0.02132 0.01225 -0.0538 0.6226 1.0000
4.500 0.7303 0.02186 0.01275 -0.0512 0.5777 1.0000
4.750 0.7527 0.02246 0.01328 -0.0489 0.5326 1.0000
5.000 0.7752 0.02314 0.01390 -0.0466 0.4877 1.0000
5.250 0.7976 0.02397 0.01464 -0.0446 0.4415 1.0000
5.500 0.8198 0.02490 0.01548 -0.0427 0.3946 1.0000
5.750 0.8420 0.02593 0.01630 -0.0409 0.3490 1.0000
6.000 0.8636 0.02724 0.01757 -0.0393 0.3021 1.0000
6.250 0.8849 0.02869 0.01889 -0.0378 0.2573 1.0000
6.500 0.9066 0.03060 0.02075 -0.0363 0.2181 1.0000
6.750 0.9285 0.03269 0.02271 -0.0351 0.1849 1.0000
7.000 0.9497 0.03510 0.02516 -0.0339 0.1573 1.0000
7.250 0.9702 0.03839 0.02899 -0.0326 0.1388 1.0000
7.500 0.9892 0.04152 0.03241 -0.0315 0.1228 1.0000
7.750 1.0055 0.04547 0.03682 -0.0304 0.1124 1.0000
8.000 1.0221 0.04973 0.04139 -0.0294 0.1065 1.0000
8.250 1.0299 0.05498 0.04721 -0.0286 0.1026 1.0000
8.500 1.0295 0.06066 0.05356 -0.0284 0.1002 1.0000
8.750 1.0245 0.06662 0.06000 -0.0287 0.0992 1.0000
9.000 1.0139 0.07301 0.06673 -0.0298 0.1002 1.0000
9.250 1.0010 0.07940 0.07331 -0.0314 0.1018 1.0000
9.500 0.9886 0.08552 0.07953 -0.0332 0.1031 1.0000
9.750 0.9804 0.09144 0.08548 -0.0347 0.1042 1.0000
10.000 0.9339 0.10847 0.10249 -0.0504 0.1307 1.0000
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Polar data table (+)
Polar graphs
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