AG14 (ag14-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG14 (ag14-il) Reynolds number: 500,000 Max Cl/Cd: 80.4 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag14-il-500000.txt Download as CSV file: xf-ag14-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG14
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4383 0.08092 0.07887 0.0050 1.0000 0.0130
-7.500 -0.4369 0.07692 0.07489 0.0036 1.0000 0.0133
-7.250 -0.4361 0.07288 0.07087 0.0020 1.0000 0.0137
-7.000 -0.4357 0.06879 0.06680 0.0002 1.0000 0.0140
-6.750 -0.4333 0.06443 0.06247 -0.0027 1.0000 0.0144
-6.500 -0.4257 0.05931 0.05735 -0.0078 1.0000 0.0149
-6.250 -0.4110 0.05407 0.05210 -0.0145 1.0000 0.0158
-6.000 -0.3934 0.04878 0.04677 -0.0207 1.0000 0.0161
-5.750 -0.3755 0.04298 0.04091 -0.0264 1.0000 0.0162
-5.500 -0.3554 0.03680 0.03461 -0.0318 1.0000 0.0163
-5.250 -0.3344 0.03056 0.02820 -0.0363 1.0000 0.0163
-3.500 -0.1690 0.01491 0.00978 -0.0476 1.0000 0.0159
-3.250 -0.1412 0.01235 0.00686 -0.0473 1.0000 0.0150
-3.000 -0.1139 0.01091 0.00523 -0.0468 1.0000 0.0150
-2.750 -0.0869 0.00997 0.00418 -0.0463 1.0000 0.0158
-2.500 -0.0592 0.00879 0.00285 -0.0461 1.0000 0.0188
-2.250 -0.0325 0.00841 0.00246 -0.0458 1.0000 0.0245
-2.000 -0.0047 0.00779 0.00185 -0.0456 1.0000 0.0449
-1.750 0.0226 0.00730 0.00163 -0.0456 1.0000 0.1129
-1.500 0.0498 0.00689 0.00154 -0.0457 1.0000 0.2025
-1.250 0.0787 0.00648 0.00147 -0.0461 0.9992 0.3114
-1.000 0.1185 0.00596 0.00142 -0.0490 0.9919 0.4618
-0.750 0.1555 0.00515 0.00140 -0.0511 0.9821 0.7026
-0.500 0.1884 0.00443 0.00130 -0.0514 0.9647 1.0000
-0.250 0.2233 0.00442 0.00119 -0.0526 0.9382 1.0000
0.000 0.2517 0.00446 0.00110 -0.0522 0.9013 1.0000
0.250 0.2768 0.00458 0.00104 -0.0511 0.8581 1.0000
0.500 0.3018 0.00476 0.00100 -0.0501 0.8126 1.0000
0.750 0.3274 0.00497 0.00099 -0.0492 0.7664 1.0000
1.000 0.3534 0.00520 0.00099 -0.0486 0.7197 1.0000
1.250 0.3798 0.00543 0.00101 -0.0481 0.6727 1.0000
1.500 0.4063 0.00568 0.00105 -0.0477 0.6271 1.0000
1.750 0.4331 0.00593 0.00112 -0.0473 0.5820 1.0000
2.000 0.4600 0.00619 0.00119 -0.0471 0.5391 1.0000
2.250 0.4869 0.00645 0.00127 -0.0468 0.4979 1.0000
2.500 0.5139 0.00671 0.00137 -0.0466 0.4588 1.0000
2.750 0.5409 0.00698 0.00149 -0.0464 0.4211 1.0000
3.000 0.5680 0.00724 0.00165 -0.0463 0.3858 1.0000
3.250 0.5950 0.00753 0.00179 -0.0461 0.3505 1.0000
3.500 0.6221 0.00780 0.00196 -0.0459 0.3184 1.0000
3.750 0.6489 0.00812 0.00214 -0.0458 0.2850 1.0000
4.000 0.6758 0.00842 0.00235 -0.0456 0.2548 1.0000
4.250 0.7027 0.00874 0.00260 -0.0455 0.2255 1.0000
4.500 0.7294 0.00910 0.00285 -0.0453 0.1949 1.0000
4.750 0.7560 0.00946 0.00312 -0.0452 0.1685 1.0000
5.000 0.7825 0.00986 0.00343 -0.0450 0.1418 1.0000
5.250 0.8089 0.01028 0.00377 -0.0448 0.1194 1.0000
5.500 0.8352 0.01072 0.00417 -0.0446 0.0988 1.0000
5.750 0.8614 0.01117 0.00458 -0.0444 0.0818 1.0000
6.000 0.8876 0.01162 0.00501 -0.0441 0.0670 1.0000
6.250 0.9135 0.01210 0.00547 -0.0439 0.0534 1.0000
6.500 0.9393 0.01263 0.00598 -0.0436 0.0411 1.0000
6.750 0.9648 0.01325 0.00663 -0.0433 0.0303 1.0000
7.000 0.9898 0.01398 0.00737 -0.0429 0.0210 1.0000
7.250 1.0134 0.01519 0.00868 -0.0422 0.0147 1.0000
7.500 1.0379 0.01603 0.00964 -0.0416 0.0120 1.0000
7.750 1.0594 0.01769 0.01146 -0.0407 0.0099 1.0000
8.000 1.0775 0.02033 0.01442 -0.0393 0.0091 1.0000
8.250 1.1013 0.02117 0.01540 -0.0388 0.0084 1.0000
8.500 1.1239 0.02225 0.01663 -0.0382 0.0076 1.0000
8.750 1.1440 0.02403 0.01864 -0.0372 0.0072 1.0000
9.000 1.1631 0.02594 0.02084 -0.0363 0.0068 1.0000
9.250 1.1810 0.02789 0.02303 -0.0354 0.0064 1.0000
9.500 1.1969 0.03008 0.02546 -0.0344 0.0060 1.0000
9.750 1.2073 0.03323 0.02893 -0.0332 0.0057 1.0000
10.000 1.2100 0.03752 0.03364 -0.0317 0.0056 1.0000
10.250 1.2073 0.04204 0.03857 -0.0304 0.0055 1.0000
10.500 1.2003 0.04640 0.04326 -0.0293 0.0055 1.0000
10.750 1.1865 0.05036 0.04748 -0.0283 0.0056 1.0000
11.000 1.1705 0.05525 0.05259 -0.0303 0.0056 1.0000
11.250 1.1568 0.06194 0.05948 -0.0362 0.0056 1.0000
11.500 1.1426 0.07094 0.06868 -0.0447 0.0057 1.0000
11.750 1.1241 0.08179 0.07971 -0.0534 0.0058 1.0000
12.000 0.9737 0.08126 0.07924 -0.0404 0.0064 1.0000
12.250 0.9332 0.09467 0.09276 -0.0460 0.0069 1.0000
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Polar data table (+)
Polar graphs
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