AG13 (ag13-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG13 (ag13-il) Reynolds number: 500,000 Max Cl/Cd: 75.24 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag13-il-500000-n5.txt Download as CSV file: xf-ag13-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5626 0.09139 0.08921 0.0142 1.0000 0.0054
-7.750 -0.5600 0.08730 0.08514 0.0117 1.0000 0.0053
-7.500 -0.5558 0.08301 0.08087 0.0083 1.0000 0.0052
-7.250 -0.5465 0.07798 0.07586 0.0029 1.0000 0.0050
-7.000 -0.5338 0.07235 0.07023 -0.0039 1.0000 0.0049
-6.750 -0.5173 0.06586 0.06372 -0.0121 1.0000 0.0048
-6.500 -0.4962 0.05822 0.05602 -0.0217 1.0000 0.0047
-6.250 -0.4707 0.04884 0.04648 -0.0320 1.0000 0.0046
-6.000 -0.4430 0.03662 0.03385 -0.0413 1.0000 0.0045
-5.750 -0.4164 0.02176 0.01782 -0.0469 1.0000 0.0048
-5.500 -0.3896 0.01810 0.01351 -0.0475 1.0000 0.0052
-5.250 -0.3628 0.01626 0.01132 -0.0475 1.0000 0.0055
-5.000 -0.3359 0.01500 0.00979 -0.0474 1.0000 0.0057
-4.750 -0.3094 0.01330 0.00783 -0.0475 1.0000 0.0065
-4.500 -0.2828 0.01279 0.00726 -0.0473 1.0000 0.0071
-4.250 -0.2559 0.01187 0.00619 -0.0471 1.0000 0.0075
-4.000 -0.2289 0.01097 0.00515 -0.0468 1.0000 0.0077
-3.750 -0.2020 0.01023 0.00428 -0.0465 1.0000 0.0081
-3.500 -0.1750 0.00965 0.00360 -0.0462 1.0000 0.0088
-3.250 -0.1482 0.00922 0.00310 -0.0459 1.0000 0.0096
-3.000 -0.1201 0.00870 0.00251 -0.0458 0.9991 0.0122
-2.750 -0.0850 0.00839 0.00218 -0.0473 0.9910 0.0170
-2.500 -0.0500 0.00803 0.00186 -0.0488 0.9799 0.0321
-2.250 -0.0155 0.00772 0.00164 -0.0502 0.9642 0.0592
-2.000 0.0185 0.00741 0.00145 -0.0515 0.9418 0.1016
-1.750 0.0482 0.00716 0.00130 -0.0517 0.9100 0.1470
-1.500 0.0742 0.00699 0.00116 -0.0511 0.8714 0.1993
-1.250 0.0995 0.00687 0.00107 -0.0503 0.8306 0.2575
-0.750 0.1517 0.00675 0.00096 -0.0493 0.7516 0.3751
-0.500 0.1782 0.00669 0.00093 -0.0489 0.7142 0.4405
-0.250 0.2049 0.00664 0.00091 -0.0486 0.6779 0.5058
0.000 0.2316 0.00657 0.00092 -0.0483 0.6423 0.5793
0.250 0.2577 0.00642 0.00094 -0.0479 0.6083 0.6768
0.500 0.2813 0.00578 0.00092 -0.0464 0.5762 0.9881
1.000 0.3364 0.00615 0.00095 -0.0461 0.5108 1.0000
1.250 0.3638 0.00634 0.00099 -0.0460 0.4786 1.0000
1.500 0.3913 0.00654 0.00104 -0.0458 0.4477 1.0000
1.750 0.4188 0.00674 0.00112 -0.0457 0.4178 1.0000
2.000 0.4463 0.00694 0.00120 -0.0456 0.3880 1.0000
2.250 0.4737 0.00717 0.00129 -0.0455 0.3568 1.0000
2.500 0.5010 0.00740 0.00140 -0.0454 0.3274 1.0000
2.750 0.5284 0.00764 0.00152 -0.0453 0.2997 1.0000
3.000 0.5557 0.00789 0.00168 -0.0452 0.2720 1.0000
3.250 0.5829 0.00815 0.00184 -0.0451 0.2452 1.0000
3.500 0.6101 0.00840 0.00201 -0.0449 0.2211 1.0000
3.750 0.6372 0.00868 0.00220 -0.0448 0.1970 1.0000
4.000 0.6642 0.00898 0.00243 -0.0447 0.1739 1.0000
4.250 0.6913 0.00926 0.00265 -0.0446 0.1543 1.0000
4.500 0.7181 0.00959 0.00291 -0.0444 0.1324 1.0000
4.750 0.7449 0.00990 0.00317 -0.0443 0.1153 1.0000
5.000 0.7715 0.01027 0.00347 -0.0441 0.0965 1.0000
5.250 0.7982 0.01063 0.00381 -0.0439 0.0815 1.0000
5.500 0.8247 0.01100 0.00416 -0.0437 0.0673 1.0000
5.750 0.8511 0.01139 0.00453 -0.0435 0.0556 1.0000
6.000 0.8773 0.01182 0.00493 -0.0433 0.0444 1.0000
6.250 0.9033 0.01228 0.00537 -0.0431 0.0337 1.0000
6.500 0.9291 0.01276 0.00584 -0.0428 0.0252 1.0000
6.750 0.9550 0.01323 0.00637 -0.0425 0.0197 1.0000
7.000 0.9804 0.01381 0.00696 -0.0422 0.0141 1.0000
7.250 1.0057 0.01440 0.00758 -0.0419 0.0104 1.0000
7.500 1.0306 0.01508 0.00836 -0.0415 0.0082 1.0000
7.750 1.0555 0.01573 0.00911 -0.0411 0.0069 1.0000
8.000 1.0797 0.01652 0.00998 -0.0407 0.0059 1.0000
8.250 1.1020 0.01781 0.01145 -0.0400 0.0050 1.0000
8.500 1.1253 0.01874 0.01258 -0.0394 0.0047 1.0000
8.750 1.1480 0.01974 0.01374 -0.0388 0.0044 1.0000
9.000 1.1705 0.02069 0.01483 -0.0382 0.0040 1.0000
9.250 1.1930 0.02158 0.01583 -0.0377 0.0036 1.0000
9.500 1.2148 0.02257 0.01695 -0.0372 0.0033 1.0000
9.750 1.2347 0.02388 0.01843 -0.0365 0.0031 1.0000
10.000 1.2523 0.02555 0.02031 -0.0356 0.0029 1.0000
10.250 1.2652 0.02801 0.02307 -0.0344 0.0027 1.0000
10.500 1.2774 0.03038 0.02572 -0.0332 0.0026 1.0000
10.750 1.2905 0.03239 0.02797 -0.0322 0.0025 1.0000
11.000 1.3001 0.03471 0.03056 -0.0310 0.0025 1.0000
11.250 1.3052 0.03739 0.03357 -0.0298 0.0024 1.0000
11.500 1.3050 0.04041 0.03687 -0.0286 0.0023 1.0000
11.750 1.2955 0.04367 0.04037 -0.0270 0.0023 1.0000
12.000 1.2819 0.04805 0.04498 -0.0280 0.0023 1.0000
12.250 1.2664 0.05449 0.05166 -0.0327 0.0023 1.0000
12.500 1.2494 0.06322 0.06061 -0.0403 0.0023 1.0000
12.750 1.2275 0.07372 0.07128 -0.0484 0.0023 1.0000
13.000 1.2030 0.08443 0.08208 -0.0552 0.0024 1.0000
13.250 1.1749 0.09544 0.09318 -0.0612 0.0024 1.0000
13.500 1.1475 0.10613 0.10394 -0.0666 0.0025 1.0000
13.750 1.1196 0.11699 0.11486 -0.0719 0.0026 1.0000
14.000 1.0914 0.12829 0.12620 -0.0773 0.0026 1.0000
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Polar data table (+)
Polar graphs
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