AG18 (ag18-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG18 (ag18-il) Reynolds number: 500,000 Max Cl/Cd: 76.99 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag18-il-500000-n5.txt Download as CSV file: xf-ag18-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG18
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5395 0.09431 0.09212 0.0127 1.0000 0.0077
-7.750 -0.5391 0.08801 0.08584 0.0090 1.0000 0.0055
-7.500 -0.5354 0.08390 0.08176 0.0060 1.0000 0.0053
-7.250 -0.5267 0.07919 0.07707 0.0012 1.0000 0.0052
-7.000 -0.5145 0.07399 0.07187 -0.0049 1.0000 0.0050
-6.750 -0.4988 0.06813 0.06600 -0.0122 1.0000 0.0049
-6.500 -0.4789 0.06135 0.05919 -0.0209 1.0000 0.0048
-6.250 -0.4546 0.05330 0.05104 -0.0306 1.0000 0.0046
-6.000 -0.4265 0.04351 0.04103 -0.0402 1.0000 0.0045
-5.750 -0.3975 0.03057 0.02750 -0.0481 1.0000 0.0045
-5.500 -0.3699 0.01989 0.01571 -0.0513 1.0000 0.0049
-5.250 -0.3430 0.01711 0.01242 -0.0516 1.0000 0.0053
-5.000 -0.3162 0.01552 0.01051 -0.0515 1.0000 0.0056
-4.750 -0.2895 0.01381 0.00848 -0.0515 1.0000 0.0061
-4.500 -0.2633 0.01302 0.00760 -0.0514 1.0000 0.0068
-4.250 -0.2369 0.01230 0.00677 -0.0511 1.0000 0.0073
-4.000 -0.2102 0.01130 0.00560 -0.0508 1.0000 0.0075
-3.750 -0.1837 0.01049 0.00465 -0.0504 1.0000 0.0078
-3.500 -0.1572 0.00984 0.00390 -0.0500 1.0000 0.0083
-3.000 -0.0871 0.00873 0.00259 -0.0530 0.9852 0.0112
-2.750 -0.0524 0.00837 0.00221 -0.0543 0.9735 0.0156
-2.500 -0.0180 0.00805 0.00188 -0.0556 0.9579 0.0277
-2.250 0.0146 0.00775 0.00164 -0.0565 0.9367 0.0521
-2.000 0.0433 0.00749 0.00146 -0.0565 0.9107 0.0885
-1.750 0.0698 0.00729 0.00131 -0.0560 0.8820 0.1314
-1.250 0.1220 0.00695 0.00109 -0.0549 0.8228 0.2463
-1.000 0.1484 0.00683 0.00103 -0.0545 0.7929 0.3085
-0.500 0.2018 0.00666 0.00095 -0.0539 0.7341 0.4317
-0.250 0.2287 0.00658 0.00093 -0.0536 0.7048 0.4967
0.000 0.2555 0.00649 0.00093 -0.0533 0.6742 0.5680
0.250 0.2818 0.00634 0.00095 -0.0529 0.6417 0.6643
0.750 0.3324 0.00585 0.00093 -0.0512 0.5742 1.0000
1.000 0.3597 0.00605 0.00096 -0.0510 0.5373 1.0000
1.250 0.3870 0.00628 0.00100 -0.0508 0.4995 1.0000
1.500 0.4143 0.00651 0.00105 -0.0507 0.4626 1.0000
1.750 0.4417 0.00673 0.00114 -0.0505 0.4273 1.0000
2.000 0.4690 0.00698 0.00122 -0.0504 0.3929 1.0000
2.250 0.4963 0.00722 0.00132 -0.0503 0.3606 1.0000
2.500 0.5236 0.00746 0.00144 -0.0502 0.3299 1.0000
2.750 0.5509 0.00771 0.00157 -0.0501 0.3011 1.0000
3.000 0.5781 0.00796 0.00173 -0.0500 0.2742 1.0000
3.250 0.6053 0.00822 0.00189 -0.0499 0.2489 1.0000
3.500 0.6325 0.00848 0.00206 -0.0498 0.2251 1.0000
3.750 0.6595 0.00876 0.00225 -0.0496 0.2025 1.0000
4.000 0.6865 0.00905 0.00248 -0.0495 0.1791 1.0000
4.250 0.7135 0.00933 0.00270 -0.0494 0.1603 1.0000
4.500 0.7403 0.00966 0.00295 -0.0492 0.1384 1.0000
4.750 0.7671 0.00997 0.00322 -0.0491 0.1214 1.0000
5.000 0.7938 0.01031 0.00350 -0.0489 0.1039 1.0000
5.250 0.8203 0.01067 0.00384 -0.0487 0.0879 1.0000
5.500 0.8467 0.01104 0.00418 -0.0485 0.0740 1.0000
5.750 0.8730 0.01145 0.00455 -0.0483 0.0608 1.0000
6.000 0.8992 0.01184 0.00494 -0.0481 0.0503 1.0000
6.250 0.9253 0.01228 0.00536 -0.0479 0.0401 1.0000
6.500 0.9511 0.01274 0.00582 -0.0476 0.0316 1.0000
6.750 0.9767 0.01326 0.00637 -0.0473 0.0236 1.0000
7.000 1.0020 0.01381 0.00692 -0.0470 0.0173 1.0000
7.250 1.0274 0.01434 0.00750 -0.0467 0.0129 1.0000
7.500 1.0520 0.01509 0.00827 -0.0463 0.0092 1.0000
7.750 1.0770 0.01567 0.00898 -0.0459 0.0078 1.0000
8.000 1.1012 0.01641 0.00979 -0.0454 0.0064 1.0000
8.250 1.1238 0.01756 0.01108 -0.0448 0.0051 1.0000
8.500 1.1479 0.01823 0.01187 -0.0443 0.0045 1.0000
8.750 1.1714 0.01899 0.01278 -0.0439 0.0039 1.0000
9.000 1.1942 0.01988 0.01379 -0.0433 0.0035 1.0000
9.250 1.2161 0.02091 0.01496 -0.0427 0.0032 1.0000
9.500 1.2361 0.02228 0.01650 -0.0419 0.0029 1.0000
9.750 1.2525 0.02427 0.01874 -0.0408 0.0027 1.0000
10.000 1.2714 0.02562 0.02029 -0.0400 0.0026 1.0000
10.250 1.2887 0.02721 0.02210 -0.0390 0.0025 1.0000
10.500 1.3037 0.02904 0.02418 -0.0379 0.0023 1.0000
10.750 1.3162 0.03113 0.02653 -0.0367 0.0022 1.0000
11.000 1.3256 0.03348 0.02915 -0.0353 0.0021 1.0000
11.250 1.3311 0.03610 0.03206 -0.0338 0.0020 1.0000
11.500 1.3317 0.03900 0.03527 -0.0323 0.0020 1.0000
11.750 1.3241 0.04201 0.03853 -0.0303 0.0019 1.0000
12.000 1.3117 0.04576 0.04251 -0.0298 0.0019 1.0000
12.250 1.2972 0.05089 0.04786 -0.0320 0.0019 1.0000
12.500 1.2805 0.05802 0.05523 -0.0372 0.0019 1.0000
12.750 1.2617 0.06722 0.06464 -0.0447 0.0019 1.0000
13.000 1.2388 0.07791 0.07551 -0.0523 0.0020 1.0000
13.250 1.2132 0.08879 0.08647 -0.0589 0.0020 1.0000
13.500 1.1865 0.09945 0.09722 -0.0645 0.0021 1.0000
13.750 1.1595 0.11006 0.10790 -0.0697 0.0022 1.0000
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Polar data table (+)
Polar graphs
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