AG36 (ag36-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG36 (ag36-il) Reynolds number: 50,000 Max Cl/Cd: 32.7 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag36-il-50000.txt Download as CSV file: xf-ag36-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4895 0.09444 0.08799 0.0018 1.0000 0.2663
-8.500 -0.4906 0.09167 0.08531 0.0005 1.0000 0.2801
-8.250 -0.4815 0.08789 0.08157 0.0013 1.0000 0.2953
-8.000 -0.4654 0.08392 0.07761 0.0039 1.0000 0.3141
-7.750 -0.4681 0.08157 0.07535 0.0029 1.0000 0.3373
-7.500 -0.4518 0.07772 0.07151 0.0064 1.0000 0.3621
-7.250 -0.4444 0.07457 0.06842 0.0083 1.0000 0.3888
-7.000 -0.4371 0.07152 0.06543 0.0103 1.0000 0.4172
-6.750 -0.4279 0.06850 0.06246 0.0130 1.0000 0.4486
-6.000 -0.3460 0.04091 0.03273 -0.0394 1.0000 0.1416
-5.750 -0.3203 0.03673 0.02781 -0.0401 1.0000 0.1316
-5.500 -0.2961 0.03370 0.02428 -0.0398 1.0000 0.1317
-5.250 -0.2707 0.03111 0.02107 -0.0394 1.0000 0.1339
-5.000 -0.2453 0.02859 0.01818 -0.0387 1.0000 0.1358
-4.750 -0.2208 0.02659 0.01607 -0.0379 1.0000 0.1425
-4.500 -0.1956 0.02490 0.01416 -0.0370 1.0000 0.1550
-4.250 -0.1695 0.02325 0.01237 -0.0361 1.0000 0.1690
-4.000 -0.1442 0.02185 0.01102 -0.0351 1.0000 0.1986
-3.750 -0.1172 0.02024 0.00969 -0.0344 1.0000 0.2615
-3.500 -0.0799 0.01576 0.00810 -0.0323 1.0000 1.0000
-3.250 -0.0584 0.01582 0.00759 -0.0314 1.0000 1.0000
-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 0.00697 -0.0291 1.0000 1.0000
-2.250 0.0255 0.01647 0.00697 -0.0285 1.0000 1.0000
-2.000 0.0461 0.01676 0.00706 -0.0280 1.0000 1.0000
-1.750 0.0663 0.01711 0.00725 -0.0276 1.0000 1.0000
-1.500 0.0859 0.01756 0.00755 -0.0273 1.0000 1.0000
-1.250 0.1046 0.01811 0.00797 -0.0272 1.0000 1.0000
-1.000 0.1225 0.01878 0.00855 -0.0273 1.0000 1.0000
-0.750 0.1396 0.01958 0.00926 -0.0276 1.0000 1.0000
-0.500 0.1594 0.02046 0.01007 -0.0285 0.9985 1.0000
-0.250 0.2249 0.02143 0.01094 -0.0374 0.9764 1.0000
0.000 0.2889 0.02223 0.01170 -0.0455 0.9552 1.0000
0.250 0.3414 0.02282 0.01232 -0.0511 0.9316 1.0000
0.500 0.3974 0.02325 0.01279 -0.0568 0.9099 1.0000
0.750 0.4475 0.02355 0.01319 -0.0610 0.8875 1.0000
1.000 0.4936 0.02373 0.01345 -0.0640 0.8657 1.0000
1.250 0.5360 0.02383 0.01365 -0.0659 0.8438 1.0000
1.500 0.5717 0.02398 0.01392 -0.0664 0.8211 1.0000
1.750 0.6067 0.02402 0.01405 -0.0663 0.7987 1.0000
2.000 0.6342 0.02428 0.01439 -0.0652 0.7742 1.0000
2.250 0.6634 0.02434 0.01452 -0.0637 0.7510 1.0000
2.500 0.6891 0.02451 0.01480 -0.0619 0.7259 1.0000
2.750 0.7130 0.02476 0.01513 -0.0600 0.6994 1.0000
3.000 0.7371 0.02494 0.01538 -0.0579 0.6728 1.0000
3.250 0.7615 0.02505 0.01554 -0.0557 0.6458 1.0000
3.500 0.7858 0.02523 0.01578 -0.0534 0.6180 1.0000
3.750 0.8094 0.02561 0.01618 -0.0513 0.5883 1.0000
4.000 0.8323 0.02616 0.01674 -0.0492 0.5569 1.0000
4.250 0.8552 0.02675 0.01732 -0.0472 0.5247 1.0000
4.500 0.8783 0.02730 0.01787 -0.0451 0.4921 1.0000
4.750 0.8990 0.02801 0.01870 -0.0433 0.4563 1.0000
5.000 0.9219 0.02836 0.01898 -0.0413 0.4221 1.0000
5.250 0.9429 0.02897 0.01961 -0.0394 0.3857 1.0000
5.500 0.9650 0.02951 0.02002 -0.0375 0.3500 1.0000
5.750 0.9844 0.03057 0.02108 -0.0357 0.3122 1.0000
6.000 1.0039 0.03173 0.02209 -0.0339 0.2748 1.0000
6.250 1.0221 0.03308 0.02326 -0.0321 0.2368 1.0000
6.500 1.0377 0.03495 0.02514 -0.0302 0.2008 1.0000
6.750 1.0543 0.03711 0.02721 -0.0285 0.1699 1.0000
7.000 1.0703 0.03979 0.03001 -0.0270 0.1465 1.0000
7.250 1.0866 0.04270 0.03308 -0.0255 0.1297 1.0000
7.500 1.1000 0.04624 0.03697 -0.0240 0.1188 1.0000
7.750 1.1151 0.04980 0.04064 -0.0228 0.1103 1.0000
8.000 1.1171 0.05394 0.04546 -0.0208 0.1052 1.0000
8.250 1.1319 0.05752 0.04907 -0.0199 0.0996 1.0000
8.500 1.1319 0.06265 0.05458 -0.0185 0.0982 1.0000
8.750 1.1227 0.06769 0.06009 -0.0169 0.0979 1.0000
9.000 1.1096 0.07281 0.06557 -0.0158 0.0979 1.0000
9.250 1.0942 0.07798 0.07099 -0.0150 0.0982 1.0000
9.500 1.0773 0.08307 0.07624 -0.0145 0.0986 1.0000
9.750 0.9701 0.09871 0.09220 -0.0275 0.1143 1.0000
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Polar data table (+)
Polar graphs
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