AG16 (ag16-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG16 (ag16-il) Reynolds number: 500,000 Max Cl/Cd: 76.27 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag16-il-500000-n5.txt Download as CSV file: xf-ag16-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5861 0.08685 0.08470 0.0070 1.0000 0.0049
-8.250 -0.5873 0.08165 0.07954 0.0036 1.0000 0.0048
-8.000 -0.5886 0.07582 0.07374 -0.0013 1.0000 0.0047
-7.750 -0.5840 0.06759 0.06553 -0.0113 1.0000 0.0046
-7.500 -0.5739 0.05125 0.04908 -0.0316 1.0000 0.0044
-7.250 -0.5726 0.02605 0.02247 -0.0478 1.0000 0.0041
-7.000 -0.5505 0.02160 0.01734 -0.0489 1.0000 0.0042
-6.750 -0.5260 0.01894 0.01425 -0.0492 1.0000 0.0044
-6.500 -0.5006 0.01705 0.01203 -0.0493 1.0000 0.0047
-6.250 -0.4747 0.01564 0.01036 -0.0492 1.0000 0.0051
-6.000 -0.4484 0.01459 0.00911 -0.0491 1.0000 0.0054
-5.750 -0.4220 0.01377 0.00815 -0.0489 1.0000 0.0056
-5.500 -0.3960 0.01244 0.00664 -0.0488 1.0000 0.0062
-5.250 -0.3696 0.01188 0.00602 -0.0486 1.0000 0.0068
-5.000 -0.3432 0.01148 0.00556 -0.0484 1.0000 0.0077
-4.750 -0.3168 0.01097 0.00498 -0.0481 1.0000 0.0085
-4.500 -0.2903 0.01043 0.00434 -0.0478 1.0000 0.0091
-4.250 -0.2637 0.00983 0.00364 -0.0475 1.0000 0.0105
-4.000 -0.2329 0.00939 0.00317 -0.0481 0.9970 0.0133
-3.750 -0.1985 0.00902 0.00276 -0.0495 0.9902 0.0190
-3.500 -0.1637 0.00865 0.00242 -0.0510 0.9819 0.0340
-3.250 -0.1301 0.00830 0.00215 -0.0523 0.9707 0.0576
-3.000 -0.0966 0.00797 0.00193 -0.0535 0.9570 0.0896
-2.750 -0.0648 0.00764 0.00173 -0.0544 0.9398 0.1325
-2.500 -0.0358 0.00738 0.00156 -0.0545 0.9177 0.1747
-2.250 -0.0087 0.00721 0.00143 -0.0541 0.8929 0.2124
-2.000 0.0177 0.00709 0.00132 -0.0536 0.8664 0.2476
-1.750 0.0440 0.00702 0.00122 -0.0531 0.8382 0.2767
-1.500 0.0706 0.00698 0.00113 -0.0526 0.8091 0.3061
-1.000 0.1242 0.00688 0.00102 -0.0519 0.7504 0.3831
-0.750 0.1513 0.00687 0.00099 -0.0516 0.7214 0.4192
-0.500 0.1785 0.00687 0.00096 -0.0514 0.6930 0.4562
-0.250 0.2058 0.00687 0.00096 -0.0512 0.6645 0.4937
0.000 0.2331 0.00687 0.00096 -0.0510 0.6367 0.5337
0.250 0.2604 0.00686 0.00098 -0.0508 0.6094 0.5768
0.500 0.2876 0.00685 0.00101 -0.0506 0.5819 0.6258
1.000 0.3402 0.00669 0.00111 -0.0497 0.5287 0.7643
1.250 0.3651 0.00633 0.00111 -0.0486 0.5023 0.9998
1.500 0.3929 0.00650 0.00117 -0.0485 0.4755 1.0000
1.750 0.4206 0.00668 0.00123 -0.0484 0.4489 1.0000
2.000 0.4482 0.00688 0.00131 -0.0483 0.4224 1.0000
2.250 0.4759 0.00708 0.00140 -0.0483 0.3960 1.0000
2.500 0.5034 0.00729 0.00150 -0.0482 0.3696 1.0000
2.750 0.5309 0.00751 0.00164 -0.0481 0.3435 1.0000
3.000 0.5584 0.00775 0.00177 -0.0480 0.3175 1.0000
3.250 0.5857 0.00800 0.00192 -0.0479 0.2903 1.0000
3.500 0.6130 0.00827 0.00209 -0.0479 0.2636 1.0000
3.750 0.6402 0.00856 0.00229 -0.0478 0.2372 1.0000
4.000 0.6674 0.00884 0.00250 -0.0477 0.2138 1.0000
4.250 0.6944 0.00915 0.00272 -0.0476 0.1889 1.0000
4.500 0.7213 0.00947 0.00296 -0.0474 0.1651 1.0000
4.750 0.7481 0.00983 0.00323 -0.0473 0.1426 1.0000
5.000 0.7749 0.01016 0.00353 -0.0472 0.1235 1.0000
5.250 0.8014 0.01057 0.00386 -0.0470 0.1008 1.0000
5.750 0.8540 0.01143 0.00458 -0.0467 0.0633 1.0000
6.000 0.8801 0.01187 0.00499 -0.0465 0.0497 1.0000
6.250 0.9060 0.01236 0.00546 -0.0462 0.0367 1.0000
6.500 0.9318 0.01286 0.00594 -0.0460 0.0268 1.0000
6.750 0.9574 0.01339 0.00646 -0.0457 0.0193 1.0000
7.000 0.9827 0.01398 0.00703 -0.0454 0.0132 1.0000
7.250 1.0081 0.01449 0.00760 -0.0451 0.0103 1.0000
7.500 1.0328 0.01520 0.00836 -0.0447 0.0077 1.0000
7.750 1.0577 0.01582 0.00907 -0.0443 0.0065 1.0000
8.000 1.0820 0.01654 0.00991 -0.0438 0.0055 1.0000
8.250 1.1047 0.01761 0.01112 -0.0432 0.0047 1.0000
8.500 1.1274 0.01862 0.01227 -0.0425 0.0044 1.0000
8.750 1.1497 0.01963 0.01343 -0.0419 0.0042 1.0000
9.000 1.1716 0.02066 0.01461 -0.0412 0.0039 1.0000
9.250 1.1934 0.02164 0.01572 -0.0406 0.0036 1.0000
9.500 1.2149 0.02258 0.01678 -0.0400 0.0033 1.0000
9.750 1.2360 0.02354 0.01786 -0.0393 0.0030 1.0000
10.000 1.2555 0.02472 0.01918 -0.0386 0.0029 1.0000
10.250 1.2728 0.02619 0.02085 -0.0376 0.0027 1.0000
10.500 1.2872 0.02801 0.02287 -0.0365 0.0026 1.0000
10.750 1.2966 0.03042 0.02555 -0.0350 0.0025 1.0000
11.000 1.3026 0.03308 0.02847 -0.0333 0.0024 1.0000
11.250 1.3105 0.03517 0.03080 -0.0319 0.0024 1.0000
11.500 1.3139 0.03747 0.03333 -0.0303 0.0023 1.0000
11.750 1.3101 0.03995 0.03602 -0.0283 0.0023 1.0000
12.000 1.3025 0.04309 0.03937 -0.0274 0.0023 1.0000
12.250 1.2927 0.04717 0.04368 -0.0283 0.0023 1.0000
12.500 1.2805 0.05256 0.04928 -0.0313 0.0022 1.0000
12.750 1.2659 0.05938 0.05631 -0.0361 0.0022 1.0000
13.000 1.2488 0.06745 0.06458 -0.0419 0.0022 1.0000
13.250 1.2284 0.07654 0.07384 -0.0480 0.0023 1.0000
13.500 1.2047 0.08641 0.08386 -0.0540 0.0023 1.0000
13.750 1.1793 0.09659 0.09415 -0.0596 0.0023 1.0000
14.000 1.1528 0.10701 0.10467 -0.0650 0.0024 1.0000
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Polar data table (+)
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