AG19 (ag19-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG19 (ag19-il) Reynolds number: 100,000 Max Cl/Cd: 51.69 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag19-il-100000.txt Download as CSV file: xf-ag19-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG19
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5287 0.10756 0.10274 0.0135 1.0000 0.0623
-8.000 -0.5285 0.10524 0.10050 0.0086 1.0000 0.0642
-7.750 -0.5268 0.10289 0.09823 0.0009 1.0000 0.0649
-7.500 -0.5171 0.09692 0.09228 0.0063 1.0000 0.0677
-7.250 -0.5076 0.09347 0.08884 0.0065 1.0000 0.0717
-7.000 -0.4993 0.08996 0.08538 0.0018 1.0000 0.0757
-6.750 -0.4774 0.08597 0.08132 -0.0193 1.0000 0.0784
-6.500 -0.4753 0.08102 0.07650 -0.0099 1.0000 0.0806
-6.250 -0.4633 0.07751 0.07301 -0.0092 1.0000 0.0845
-6.000 -0.4305 0.07194 0.06723 -0.0290 1.0000 0.0923
-5.750 -0.4262 0.06816 0.06362 -0.0217 1.0000 0.0948
-5.500 -0.4070 0.06446 0.05984 -0.0246 1.0000 0.1023
-5.250 -0.3853 0.05964 0.05495 -0.0296 1.0000 0.1088
-5.000 -0.3577 0.05506 0.05019 -0.0362 1.0000 0.1206
-4.750 -0.3402 0.05198 0.04715 -0.0355 1.0000 0.1282
-4.500 -0.3125 0.04819 0.04316 -0.0398 1.0000 0.1444
-4.250 -0.2909 0.04465 0.03960 -0.0407 1.0000 0.1554
-4.000 -0.2648 0.04117 0.03596 -0.0433 1.0000 0.1763
-3.750 -0.1996 0.02863 0.02161 -0.0517 1.0000 0.0625
-3.500 -0.1702 0.02527 0.01777 -0.0521 1.0000 0.0603
-3.250 -0.1407 0.02275 0.01471 -0.0521 1.0000 0.0623
-3.000 -0.1114 0.02029 0.01178 -0.0518 1.0000 0.0621
-2.750 -0.0827 0.01842 0.00949 -0.0511 1.0000 0.0644
-2.500 -0.0559 0.01678 0.00777 -0.0507 1.0000 0.0756
-2.250 -0.0286 0.01532 0.00628 -0.0500 1.0000 0.0923
-2.000 -0.0019 0.01388 0.00516 -0.0497 1.0000 0.1396
-1.750 0.0249 0.01174 0.00436 -0.0499 1.0000 0.3988
-1.500 0.0429 0.00982 0.00399 -0.0464 1.0000 1.0000
-1.250 0.0697 0.00985 0.00362 -0.0461 1.0000 1.0000
-1.000 0.0960 0.00991 0.00341 -0.0459 1.0000 1.0000
-0.750 0.1221 0.00998 0.00327 -0.0457 1.0000 1.0000
-0.500 0.1478 0.01007 0.00320 -0.0454 1.0000 1.0000
-0.250 0.1734 0.01020 0.00319 -0.0453 1.0000 1.0000
0.000 0.1988 0.01035 0.00322 -0.0451 1.0000 1.0000
0.250 0.2241 0.01054 0.00333 -0.0451 1.0000 1.0000
0.500 0.2492 0.01077 0.00350 -0.0451 1.0000 1.0000
0.750 0.2739 0.01105 0.00375 -0.0453 1.0000 1.0000
1.000 0.2981 0.01140 0.00409 -0.0455 1.0000 1.0000
1.250 0.3493 0.01166 0.00437 -0.0508 0.9845 1.0000
1.500 0.4079 0.01173 0.00450 -0.0570 0.9616 1.0000
1.750 0.4592 0.01167 0.00452 -0.0611 0.9356 1.0000
2.000 0.5002 0.01157 0.00452 -0.0626 0.9043 1.0000
2.250 0.5314 0.01153 0.00450 -0.0619 0.8675 1.0000
2.500 0.5568 0.01156 0.00450 -0.0599 0.8262 1.0000
2.750 0.5799 0.01166 0.00452 -0.0576 0.7807 1.0000
3.000 0.6024 0.01186 0.00465 -0.0553 0.7298 1.0000
3.250 0.6250 0.01214 0.00476 -0.0531 0.6733 1.0000
3.500 0.6477 0.01253 0.00491 -0.0513 0.6120 1.0000
3.750 0.6707 0.01303 0.00514 -0.0497 0.5476 1.0000
4.000 0.6941 0.01365 0.00547 -0.0484 0.4856 1.0000
4.250 0.7177 0.01434 0.00596 -0.0474 0.4286 1.0000
4.500 0.7416 0.01511 0.00648 -0.0465 0.3774 1.0000
4.750 0.7656 0.01591 0.00709 -0.0458 0.3306 1.0000
5.000 0.7896 0.01678 0.00778 -0.0451 0.2883 1.0000
5.250 0.8138 0.01769 0.00856 -0.0445 0.2495 1.0000
5.500 0.8378 0.01871 0.00943 -0.0438 0.2165 1.0000
5.750 0.8621 0.01975 0.01050 -0.0432 0.1861 1.0000
6.000 0.8861 0.02092 0.01162 -0.0426 0.1607 1.0000
6.250 0.9100 0.02220 0.01283 -0.0419 0.1386 1.0000
6.500 0.9339 0.02358 0.01436 -0.0412 0.1180 1.0000
6.750 0.9576 0.02520 0.01602 -0.0404 0.1012 1.0000
7.000 0.9804 0.02706 0.01786 -0.0398 0.0858 1.0000
7.250 1.0033 0.02918 0.02028 -0.0389 0.0734 1.0000
7.500 1.0251 0.03146 0.02296 -0.0378 0.0629 1.0000
7.750 1.0447 0.03520 0.02718 -0.0366 0.0568 1.0000
8.000 1.0638 0.03726 0.02936 -0.0359 0.0489 1.0000
8.250 1.0764 0.04251 0.03527 -0.0346 0.0469 1.0000
8.500 1.0852 0.04763 0.04116 -0.0332 0.0460 1.0000
8.750 1.0881 0.05336 0.04752 -0.0322 0.0459 1.0000
9.000 1.0855 0.05920 0.05387 -0.0316 0.0458 1.0000
9.250 1.0777 0.06506 0.06013 -0.0316 0.0459 1.0000
9.500 1.0658 0.07082 0.06616 -0.0321 0.0463 1.0000
9.750 1.0512 0.07629 0.07179 -0.0329 0.0468 1.0000
10.000 1.0364 0.08187 0.07745 -0.0344 0.0473 1.0000
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Polar data table (+)
Polar graphs
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