AG36 (ag36-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG36 (ag36-il) Reynolds number: 50,000 Max Cl/Cd: 36.87 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag36-il-50000-n5.txt Download as CSV file: xf-ag36-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG36
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5036 0.11298 0.10600 -0.0001 1.0000 0.1140
-10.250 -0.5085 0.11017 0.10328 -0.0035 1.0000 0.1189
-10.000 -0.5206 0.10756 0.10081 -0.0091 1.0000 0.1203
-9.500 -0.5025 0.09283 0.08602 -0.0153 1.0000 0.0633
-9.250 -0.4963 0.08883 0.08205 -0.0159 1.0000 0.0605
-8.750 -0.4933 0.07485 0.06795 -0.0319 1.0000 0.0518
-8.500 -0.4845 0.07082 0.06392 -0.0326 1.0000 0.0511
-8.250 -0.4758 0.06637 0.05941 -0.0343 1.0000 0.0503
-8.000 -0.4661 0.06173 0.05464 -0.0363 1.0000 0.0496
-7.750 -0.4549 0.05702 0.04974 -0.0382 1.0000 0.0490
-7.500 -0.4418 0.05238 0.04480 -0.0398 1.0000 0.0486
-7.250 -0.4267 0.04792 0.03996 -0.0410 1.0000 0.0490
-7.000 -0.4095 0.04377 0.03529 -0.0417 1.0000 0.0503
-6.750 -0.3900 0.04010 0.03099 -0.0418 1.0000 0.0516
-6.500 -0.3697 0.03683 0.02727 -0.0415 1.0000 0.0524
-6.250 -0.3487 0.03400 0.02412 -0.0410 1.0000 0.0534
-6.000 -0.3266 0.03163 0.02145 -0.0404 1.0000 0.0549
-5.500 -0.2799 0.02800 0.01710 -0.0388 1.0000 0.0631
-5.250 -0.2557 0.02619 0.01501 -0.0379 1.0000 0.0661
-5.000 -0.2323 0.02478 0.01353 -0.0370 1.0000 0.0709
-4.750 -0.2082 0.02362 0.01215 -0.0360 1.0000 0.0794
-4.500 -0.1841 0.02248 0.01095 -0.0352 1.0000 0.0881
-4.250 -0.1601 0.02153 0.00993 -0.0344 1.0000 0.1032
-4.000 -0.1358 0.02055 0.00899 -0.0339 1.0000 0.1260
-3.750 -0.1112 0.01943 0.00822 -0.0336 1.0000 0.1834
-3.250 -0.0749 0.01632 0.00766 -0.0295 1.0000 0.7067
-3.000 -0.0373 0.01591 0.00728 -0.0305 1.0000 1.0000
-2.750 -0.0163 0.01605 0.00709 -0.0298 1.0000 1.0000
-2.500 0.0047 0.01624 0.00698 -0.0291 1.0000 1.0000
-2.250 0.0364 0.01647 0.00693 -0.0305 0.9942 1.0000
-2.000 0.0819 0.01667 0.00686 -0.0346 0.9786 1.0000
-1.750 0.1270 0.01686 0.00681 -0.0384 0.9625 1.0000
-1.500 0.1720 0.01701 0.00679 -0.0420 0.9461 1.0000
-1.250 0.2164 0.01713 0.00677 -0.0454 0.9291 1.0000
-1.000 0.2569 0.01721 0.00674 -0.0479 0.9099 1.0000
-0.750 0.2939 0.01727 0.00673 -0.0495 0.8883 1.0000
-0.500 0.3310 0.01731 0.00669 -0.0509 0.8677 1.0000
-0.250 0.3647 0.01737 0.00669 -0.0516 0.8454 1.0000
0.000 0.3971 0.01745 0.00670 -0.0520 0.8238 1.0000
0.250 0.4264 0.01758 0.00677 -0.0518 0.8008 1.0000
0.500 0.4546 0.01774 0.00689 -0.0513 0.7786 1.0000
0.750 0.4816 0.01793 0.00702 -0.0507 0.7561 1.0000
1.000 0.5078 0.01814 0.00720 -0.0500 0.7338 1.0000
1.250 0.5336 0.01836 0.00739 -0.0491 0.7117 1.0000
1.500 0.5588 0.01861 0.00766 -0.0483 0.6890 1.0000
1.750 0.5842 0.01884 0.00787 -0.0474 0.6670 1.0000
2.000 0.6093 0.01909 0.00811 -0.0465 0.6449 1.0000
2.250 0.6347 0.01934 0.00830 -0.0456 0.6243 1.0000
2.500 0.6598 0.01968 0.00867 -0.0447 0.6020 1.0000
2.750 0.6853 0.02005 0.00900 -0.0439 0.5804 1.0000
3.000 0.7101 0.02049 0.00949 -0.0432 0.5566 1.0000
3.250 0.7350 0.02093 0.00995 -0.0424 0.5335 1.0000
3.500 0.7593 0.02139 0.01051 -0.0416 0.5092 1.0000
3.750 0.7831 0.02184 0.01106 -0.0408 0.4836 1.0000
4.000 0.8066 0.02229 0.01161 -0.0399 0.4569 1.0000
4.250 0.8297 0.02272 0.01213 -0.0390 0.4293 1.0000
4.500 0.8524 0.02319 0.01270 -0.0380 0.4006 1.0000
4.750 0.8746 0.02372 0.01329 -0.0370 0.3708 1.0000
5.000 0.8963 0.02435 0.01394 -0.0360 0.3403 1.0000
5.250 0.9172 0.02510 0.01469 -0.0350 0.3096 1.0000
5.500 0.9374 0.02597 0.01558 -0.0339 0.2790 1.0000
5.750 0.9569 0.02696 0.01656 -0.0329 0.2485 1.0000
6.000 0.9755 0.02806 0.01770 -0.0319 0.2181 1.0000
6.250 0.9929 0.02931 0.01895 -0.0308 0.1887 1.0000
6.500 1.0089 0.03071 0.02035 -0.0297 0.1602 1.0000
6.750 1.0234 0.03230 0.02191 -0.0286 0.1339 1.0000
7.000 1.0362 0.03408 0.02367 -0.0273 0.1121 1.0000
7.250 1.0492 0.03604 0.02574 -0.0259 0.0935 1.0000
7.500 1.0612 0.03811 0.02789 -0.0245 0.0800 1.0000
7.750 1.0725 0.04027 0.03013 -0.0231 0.0701 1.0000
8.000 1.0832 0.04244 0.03238 -0.0217 0.0626 1.0000
8.250 1.0957 0.04503 0.03527 -0.0202 0.0568 1.0000
8.500 1.1044 0.04733 0.03769 -0.0189 0.0519 1.0000
8.750 1.1127 0.05014 0.04074 -0.0176 0.0486 1.0000
9.000 1.1188 0.05349 0.04452 -0.0161 0.0462 1.0000
9.250 1.1187 0.05671 0.04807 -0.0145 0.0443 1.0000
9.500 1.1152 0.05987 0.05147 -0.0131 0.0427 1.0000
9.750 1.1105 0.06307 0.05483 -0.0123 0.0412 1.0000
10.000 1.1064 0.06650 0.05833 -0.0119 0.0399 1.0000
10.250 1.0941 0.07108 0.06314 -0.0125 0.0394 1.0000
10.500 1.0778 0.07645 0.06880 -0.0142 0.0392 1.0000
10.750 1.0601 0.08253 0.07513 -0.0170 0.0392 1.0000
11.000 1.0417 0.08936 0.08214 -0.0207 0.0393 1.0000
11.250 1.0229 0.09680 0.08974 -0.0250 0.0395 1.0000
11.500 0.9470 0.12137 0.11464 -0.0417 0.0461 1.0000
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Polar data table (+)
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