AG19 (ag19-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG19 (ag19-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.44 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag19-il-1000000.txt Download as CSV file: xf-ag19-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5380 0.09016 0.08864 0.0113 1.0000 0.0060
-7.500 -0.5337 0.08614 0.08463 0.0085 1.0000 0.0061
-7.250 -0.5236 0.08209 0.08059 0.0044 1.0000 0.0062
-7.000 -0.5107 0.07794 0.07645 -0.0002 1.0000 0.0064
-6.750 -0.4953 0.07365 0.07215 -0.0053 1.0000 0.0065
-6.500 -0.4773 0.06904 0.06753 -0.0112 1.0000 0.0067
-6.250 -0.4565 0.06407 0.06255 -0.0176 1.0000 0.0068
-6.000 -0.4327 0.05873 0.05716 -0.0245 1.0000 0.0071
-5.750 -0.4062 0.05298 0.05135 -0.0314 1.0000 0.0074
-5.500 -0.3775 0.04687 0.04512 -0.0379 1.0000 0.0078
-5.250 -0.3474 0.04050 0.03859 -0.0434 1.0000 0.0083
-5.000 -0.3166 0.03490 0.03279 -0.0467 1.0000 0.0094
-4.500 -0.2552 0.01605 0.01242 -0.0525 1.0000 0.0072
-4.250 -0.2288 0.01495 0.01115 -0.0523 1.0000 0.0081
-4.000 -0.2020 0.01318 0.00909 -0.0521 1.0000 0.0085
-3.750 -0.1752 0.01160 0.00725 -0.0517 1.0000 0.0086
-3.500 -0.1492 0.01088 0.00642 -0.0512 1.0000 0.0092
-3.250 -0.1231 0.01003 0.00545 -0.0506 1.0000 0.0095
-3.000 -0.0921 0.00868 0.00394 -0.0511 0.9988 0.0094
-2.750 -0.0549 0.00776 0.00288 -0.0530 0.9953 0.0095
-2.500 -0.0190 0.00727 0.00230 -0.0545 0.9897 0.0100
-2.250 0.0175 0.00659 0.00150 -0.0562 0.9819 0.0166
-2.000 0.0514 0.00621 0.00118 -0.0573 0.9688 0.0409
-1.750 0.0815 0.00592 0.00103 -0.0577 0.9480 0.0835
-1.500 0.1081 0.00568 0.00091 -0.0572 0.9220 0.1414
-1.250 0.1337 0.00550 0.00082 -0.0565 0.8937 0.2058
-1.000 0.1596 0.00532 0.00076 -0.0560 0.8650 0.2835
-0.750 0.1860 0.00513 0.00073 -0.0556 0.8356 0.3775
-0.500 0.2125 0.00497 0.00071 -0.0552 0.8057 0.4720
-0.250 0.2391 0.00475 0.00070 -0.0550 0.7759 0.5938
0.000 0.2622 0.00411 0.00073 -0.0538 0.7468 0.8431
0.250 0.2892 0.00395 0.00068 -0.0532 0.7164 1.0000
0.500 0.3166 0.00410 0.00068 -0.0530 0.6842 1.0000
0.750 0.3441 0.00426 0.00068 -0.0528 0.6479 1.0000
1.000 0.3715 0.00445 0.00070 -0.0526 0.6090 1.0000
1.250 0.3989 0.00465 0.00073 -0.0524 0.5669 1.0000
1.500 0.4262 0.00488 0.00077 -0.0523 0.5232 1.0000
1.750 0.4535 0.00513 0.00084 -0.0521 0.4775 1.0000
2.000 0.4808 0.00538 0.00092 -0.0520 0.4333 1.0000
2.250 0.5082 0.00564 0.00100 -0.0519 0.3926 1.0000
2.500 0.5355 0.00588 0.00110 -0.0518 0.3558 1.0000
2.750 0.5629 0.00613 0.00121 -0.0517 0.3218 1.0000
3.000 0.5903 0.00635 0.00134 -0.0516 0.2942 1.0000
3.250 0.6175 0.00660 0.00147 -0.0515 0.2643 1.0000
3.500 0.6449 0.00684 0.00161 -0.0514 0.2394 1.0000
3.750 0.6721 0.00708 0.00176 -0.0513 0.2151 1.0000
4.000 0.6992 0.00736 0.00193 -0.0512 0.1892 1.0000
4.250 0.7263 0.00761 0.00213 -0.0511 0.1679 1.0000
4.500 0.7533 0.00790 0.00233 -0.0509 0.1453 1.0000
5.000 0.8071 0.00850 0.00279 -0.0507 0.1078 1.0000
5.250 0.8339 0.00882 0.00304 -0.0505 0.0907 1.0000
5.500 0.8606 0.00915 0.00334 -0.0503 0.0765 1.0000
5.750 0.8871 0.00950 0.00363 -0.0502 0.0634 1.0000
6.000 0.9137 0.00984 0.00395 -0.0500 0.0523 1.0000
6.250 0.9401 0.01020 0.00428 -0.0498 0.0423 1.0000
6.500 0.9663 0.01059 0.00464 -0.0496 0.0329 1.0000
6.750 0.9923 0.01103 0.00507 -0.0493 0.0246 1.0000
7.000 1.0178 0.01162 0.00566 -0.0490 0.0164 1.0000
7.250 1.0437 0.01203 0.00607 -0.0487 0.0127 1.0000
7.500 1.0689 0.01266 0.00675 -0.0483 0.0087 1.0000
7.750 1.0938 0.01336 0.00748 -0.0479 0.0063 1.0000
8.000 1.1176 0.01438 0.00867 -0.0473 0.0051 1.0000
8.250 1.1424 0.01502 0.00941 -0.0468 0.0047 1.0000
8.500 1.1667 0.01575 0.01023 -0.0464 0.0042 1.0000
8.750 1.1907 0.01649 0.01109 -0.0459 0.0037 1.0000
9.000 1.2113 0.01803 0.01281 -0.0451 0.0031 1.0000
9.250 1.2265 0.02077 0.01593 -0.0435 0.0027 1.0000
9.500 1.2468 0.02218 0.01753 -0.0427 0.0027 1.0000
9.750 1.2644 0.02407 0.01965 -0.0416 0.0026 1.0000
10.000 1.2791 0.02641 0.02228 -0.0403 0.0025 1.0000
10.250 1.2902 0.02923 0.02542 -0.0388 0.0025 1.0000
10.500 1.2968 0.03254 0.02907 -0.0372 0.0025 1.0000
10.750 1.2974 0.03633 0.03321 -0.0354 0.0025 1.0000
11.000 1.2907 0.04051 0.03773 -0.0337 0.0026 1.0000
11.250 1.2754 0.04445 0.04193 -0.0316 0.0026 1.0000
11.500 1.2568 0.04906 0.04674 -0.0320 0.0026 1.0000
11.750 1.2391 0.05558 0.05347 -0.0366 0.0026 1.0000
12.000 1.2213 0.06474 0.06282 -0.0449 0.0026 1.0000
12.250 1.2040 0.07519 0.07342 -0.0534 0.0026 1.0000
12.500 1.1832 0.08587 0.08421 -0.0604 0.0026 1.0000
12.750 1.1605 0.09626 0.09468 -0.0661 0.0026 1.0000
13.000 1.1359 0.10672 0.10519 -0.0713 0.0027 1.0000
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Polar data table (+)
Polar graphs
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