AG13 (ag13-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG13 (ag13-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.19 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag13-il-1000000-n5.txt Download as CSV file: xf-ag13-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5701 0.09626 0.09470 0.0184 1.0000 0.0044
-7.500 -0.5655 0.07944 0.07793 0.0068 1.0000 0.0029
-7.250 -0.5546 0.07318 0.07169 -0.0008 1.0000 0.0029
-6.750 -0.5203 0.01975 0.01655 -0.0474 1.0000 0.0027
-6.500 -0.4948 0.01672 0.01305 -0.0480 1.0000 0.0029
-6.250 -0.4683 0.01539 0.01148 -0.0481 1.0000 0.0030
-6.000 -0.4420 0.01303 0.00869 -0.0484 1.0000 0.0033
-5.750 -0.4152 0.01221 0.00775 -0.0484 1.0000 0.0036
-5.500 -0.3882 0.01166 0.00711 -0.0483 1.0000 0.0038
-5.250 -0.3612 0.01106 0.00640 -0.0481 1.0000 0.0040
-5.000 -0.3342 0.01045 0.00569 -0.0480 1.0000 0.0042
-4.750 -0.3071 0.00987 0.00502 -0.0478 1.0000 0.0044
-4.500 -0.2801 0.00932 0.00438 -0.0476 1.0000 0.0046
-4.250 -0.2531 0.00895 0.00395 -0.0473 1.0000 0.0050
-4.000 -0.2220 0.00858 0.00353 -0.0480 0.9958 0.0054
-3.750 -0.1889 0.00814 0.00300 -0.0491 0.9871 0.0056
-3.500 -0.1552 0.00767 0.00244 -0.0502 0.9744 0.0059
-3.250 -0.1221 0.00725 0.00194 -0.0512 0.9549 0.0074
-3.000 -0.0940 0.00708 0.00169 -0.0510 0.9242 0.0089
-2.500 -0.0428 0.00694 0.00127 -0.0494 0.8456 0.0180
-2.250 -0.0164 0.00687 0.00112 -0.0489 0.8050 0.0332
-2.000 0.0106 0.00683 0.00099 -0.0486 0.7663 0.0497
-1.750 0.0378 0.00676 0.00088 -0.0484 0.7293 0.0797
-1.500 0.0652 0.00669 0.00078 -0.0483 0.6939 0.1148
-1.250 0.0928 0.00663 0.00071 -0.0482 0.6602 0.1522
-1.000 0.1204 0.00657 0.00066 -0.0481 0.6275 0.1967
-0.750 0.1481 0.00652 0.00062 -0.0481 0.5958 0.2419
-0.500 0.1758 0.00647 0.00060 -0.0481 0.5653 0.2912
-0.250 0.2036 0.00643 0.00059 -0.0481 0.5357 0.3398
0.000 0.2313 0.00640 0.00059 -0.0481 0.5069 0.3923
0.250 0.2590 0.00640 0.00061 -0.0480 0.4780 0.4405
0.500 0.2867 0.00638 0.00064 -0.0480 0.4494 0.4960
0.750 0.3143 0.00636 0.00068 -0.0480 0.4218 0.5572
1.000 0.3417 0.00629 0.00074 -0.0479 0.3951 0.6361
1.250 0.3684 0.00611 0.00081 -0.0477 0.3694 0.7515
1.500 0.3926 0.00568 0.00084 -0.0466 0.3452 1.0000
1.750 0.4203 0.00586 0.00091 -0.0465 0.3180 1.0000
2.000 0.4480 0.00605 0.00098 -0.0464 0.2925 1.0000
2.250 0.4756 0.00624 0.00106 -0.0464 0.2692 1.0000
2.500 0.5033 0.00643 0.00116 -0.0463 0.2456 1.0000
2.750 0.5308 0.00663 0.00126 -0.0462 0.2226 1.0000
3.000 0.5584 0.00684 0.00140 -0.0461 0.2021 1.0000
3.250 0.5859 0.00705 0.00153 -0.0460 0.1811 1.0000
3.500 0.6132 0.00729 0.00167 -0.0459 0.1610 1.0000
3.750 0.6407 0.00749 0.00182 -0.0458 0.1454 1.0000
4.000 0.6679 0.00775 0.00201 -0.0457 0.1248 1.0000
4.250 0.6952 0.00799 0.00220 -0.0456 0.1105 1.0000
4.500 0.7223 0.00826 0.00240 -0.0455 0.0941 1.0000
4.750 0.7494 0.00853 0.00262 -0.0454 0.0806 1.0000
5.000 0.7764 0.00882 0.00285 -0.0452 0.0669 1.0000
5.250 0.8034 0.00911 0.00312 -0.0451 0.0562 1.0000
5.500 0.8302 0.00942 0.00340 -0.0449 0.0453 1.0000
5.750 0.8568 0.00977 0.00370 -0.0447 0.0347 1.0000
6.000 0.8834 0.01011 0.00402 -0.0446 0.0272 1.0000
6.250 0.9099 0.01047 0.00436 -0.0444 0.0202 1.0000
6.500 0.9362 0.01087 0.00474 -0.0441 0.0143 1.0000
6.750 0.9624 0.01126 0.00516 -0.0439 0.0110 1.0000
7.000 0.9885 0.01166 0.00558 -0.0437 0.0082 1.0000
7.250 1.0145 0.01211 0.00604 -0.0434 0.0064 1.0000
7.500 1.0401 0.01262 0.00661 -0.0431 0.0049 1.0000
7.750 1.0659 0.01307 0.00711 -0.0428 0.0043 1.0000
8.000 1.0912 0.01357 0.00766 -0.0425 0.0036 1.0000
8.250 1.1160 0.01422 0.00838 -0.0421 0.0029 1.0000
8.500 1.1404 0.01494 0.00924 -0.0417 0.0026 1.0000
8.750 1.1651 0.01554 0.00992 -0.0413 0.0025 1.0000
9.000 1.1894 0.01620 0.01068 -0.0409 0.0023 1.0000
9.250 1.2132 0.01693 0.01152 -0.0404 0.0022 1.0000
9.500 1.2366 0.01771 0.01241 -0.0399 0.0021 1.0000
9.750 1.2595 0.01854 0.01336 -0.0394 0.0020 1.0000
10.000 1.2820 0.01941 0.01434 -0.0388 0.0019 1.0000
10.250 1.3041 0.02031 0.01537 -0.0383 0.0018 1.0000
10.500 1.3256 0.02126 0.01643 -0.0377 0.0017 1.0000
10.750 1.3465 0.02225 0.01758 -0.0370 0.0016 1.0000
11.000 1.3662 0.02341 0.01886 -0.0363 0.0015 1.0000
11.250 1.3837 0.02487 0.02049 -0.0355 0.0014 1.0000
11.500 1.3950 0.02725 0.02316 -0.0341 0.0012 1.0000
11.750 1.4031 0.02988 0.02608 -0.0327 0.0011 1.0000
12.000 1.4153 0.03163 0.02801 -0.0316 0.0011 1.0000
12.250 1.4242 0.03364 0.03021 -0.0304 0.0011 1.0000
12.500 1.4294 0.03587 0.03263 -0.0291 0.0011 1.0000
12.750 1.4258 0.03844 0.03539 -0.0272 0.0011 1.0000
13.000 1.4156 0.04158 0.03872 -0.0261 0.0011 1.0000
13.250 1.4004 0.04657 0.04391 -0.0282 0.0011 1.0000
13.500 1.3832 0.05403 0.05158 -0.0342 0.0011 1.0000
13.750 1.3579 0.06506 0.06283 -0.0433 0.0011 1.0000
14.000 1.3190 0.07893 0.07688 -0.0524 0.0011 1.0000
14.250 1.2718 0.09353 0.09161 -0.0602 0.0011 1.0000
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Polar data table (+)
Polar graphs
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