AG19 (ag19-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG19 (ag19-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.93 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag19-il-1000000-n5.txt Download as CSV file: xf-ag19-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5721 0.12191 0.12028 0.0273 1.0000 0.0055
-9.500 -0.5669 0.11817 0.11654 0.0256 1.0000 0.0055
-7.000 -0.5134 0.07577 0.07425 -0.0010 1.0000 0.0029
-6.750 -0.4974 0.06987 0.06835 -0.0084 1.0000 0.0028
-6.500 -0.4770 0.06328 0.06173 -0.0170 1.0000 0.0028
-6.250 -0.4517 0.05549 0.05387 -0.0269 1.0000 0.0027
-6.000 -0.4210 0.04521 0.04342 -0.0382 1.0000 0.0027
-5.750 -0.3849 0.01718 0.01376 -0.0527 1.0000 0.0030
-5.500 -0.3582 0.01346 0.00940 -0.0534 1.0000 0.0035
-5.250 -0.3315 0.01271 0.00852 -0.0533 1.0000 0.0037
-5.000 -0.3047 0.01197 0.00766 -0.0532 1.0000 0.0039
-4.750 -0.2780 0.01126 0.00682 -0.0530 1.0000 0.0041
-4.500 -0.2512 0.01048 0.00591 -0.0528 1.0000 0.0043
-4.250 -0.2223 0.00980 0.00511 -0.0530 0.9983 0.0045
-4.000 -0.1888 0.00935 0.00458 -0.0542 0.9918 0.0050
-3.750 -0.1547 0.00878 0.00391 -0.0556 0.9815 0.0053
-3.500 -0.1212 0.00814 0.00315 -0.0566 0.9648 0.0054
-3.250 -0.0909 0.00770 0.00257 -0.0569 0.9375 0.0055
-3.000 -0.0649 0.00745 0.00216 -0.0562 0.9045 0.0057
-2.750 -0.0389 0.00715 0.00166 -0.0554 0.8721 0.0069
-2.500 -0.0124 0.00704 0.00142 -0.0549 0.8408 0.0090
-2.250 0.0145 0.00696 0.00122 -0.0545 0.8101 0.0127
-2.000 0.0417 0.00690 0.00107 -0.0542 0.7808 0.0201
-1.750 0.0691 0.00681 0.00094 -0.0540 0.7532 0.0365
-1.500 0.0966 0.00672 0.00083 -0.0538 0.7260 0.0607
-1.250 0.1242 0.00665 0.00074 -0.0537 0.6987 0.0914
-1.000 0.1519 0.00657 0.00067 -0.0536 0.6704 0.1305
-0.750 0.1795 0.00650 0.00063 -0.0536 0.6399 0.1775
-0.500 0.2071 0.00647 0.00060 -0.0535 0.6066 0.2215
-0.250 0.2347 0.00643 0.00058 -0.0535 0.5719 0.2789
0.000 0.2622 0.00638 0.00058 -0.0535 0.5351 0.3469
0.250 0.2897 0.00635 0.00061 -0.0535 0.4984 0.4186
0.500 0.3172 0.00634 0.00065 -0.0535 0.4616 0.4912
0.750 0.3445 0.00632 0.00070 -0.0535 0.4239 0.5730
1.000 0.3716 0.00621 0.00077 -0.0534 0.3906 0.6808
1.500 0.4226 0.00580 0.00087 -0.0521 0.3325 1.0000
1.750 0.4503 0.00599 0.00094 -0.0520 0.3053 1.0000
2.000 0.4779 0.00618 0.00102 -0.0520 0.2800 1.0000
2.250 0.5054 0.00637 0.00110 -0.0519 0.2565 1.0000
2.500 0.5330 0.00656 0.00120 -0.0518 0.2351 1.0000
2.750 0.5605 0.00676 0.00130 -0.0517 0.2132 1.0000
3.000 0.5881 0.00694 0.00143 -0.0516 0.1961 1.0000
3.250 0.6154 0.00717 0.00157 -0.0515 0.1749 1.0000
3.500 0.6428 0.00738 0.00170 -0.0514 0.1575 1.0000
3.750 0.6701 0.00760 0.00186 -0.0513 0.1410 1.0000
4.000 0.6973 0.00786 0.00203 -0.0512 0.1226 1.0000
4.250 0.7245 0.00809 0.00223 -0.0511 0.1096 1.0000
4.500 0.7516 0.00834 0.00243 -0.0509 0.0949 1.0000
4.750 0.7787 0.00860 0.00265 -0.0508 0.0822 1.0000
5.000 0.8056 0.00887 0.00288 -0.0507 0.0713 1.0000
5.250 0.8325 0.00917 0.00313 -0.0505 0.0595 1.0000
5.500 0.8593 0.00945 0.00341 -0.0503 0.0510 1.0000
5.750 0.8860 0.00975 0.00369 -0.0502 0.0423 1.0000
6.000 0.9125 0.01009 0.00400 -0.0500 0.0340 1.0000
6.250 0.9388 0.01047 0.00435 -0.0498 0.0255 1.0000
6.500 0.9651 0.01085 0.00471 -0.0496 0.0197 1.0000
6.750 0.9913 0.01122 0.00509 -0.0493 0.0150 1.0000
7.000 1.0172 0.01167 0.00555 -0.0491 0.0109 1.0000
7.250 1.0431 0.01208 0.00599 -0.0488 0.0082 1.0000
7.500 1.0685 0.01262 0.00654 -0.0485 0.0054 1.0000
7.750 1.0942 0.01304 0.00701 -0.0482 0.0045 1.0000
8.000 1.1194 0.01357 0.00757 -0.0479 0.0036 1.0000
8.250 1.1441 0.01425 0.00833 -0.0475 0.0028 1.0000
8.500 1.1692 0.01476 0.00893 -0.0472 0.0026 1.0000
8.750 1.1939 0.01534 0.00962 -0.0468 0.0024 1.0000
9.000 1.2182 0.01597 0.01034 -0.0464 0.0021 1.0000
9.250 1.2422 0.01664 0.01110 -0.0459 0.0019 1.0000
9.500 1.2658 0.01738 0.01193 -0.0455 0.0017 1.0000
9.750 1.2885 0.01826 0.01292 -0.0449 0.0015 1.0000
10.000 1.3080 0.01983 0.01472 -0.0440 0.0013 1.0000
10.250 1.3290 0.02093 0.01597 -0.0433 0.0012 1.0000
10.500 1.3497 0.02201 0.01720 -0.0426 0.0012 1.0000
10.750 1.3692 0.02325 0.01860 -0.0418 0.0011 1.0000
11.000 1.3872 0.02466 0.02020 -0.0409 0.0011 1.0000
11.250 1.4036 0.02625 0.02202 -0.0399 0.0011 1.0000
11.500 1.4177 0.02806 0.02404 -0.0388 0.0010 1.0000
11.750 1.4292 0.03009 0.02630 -0.0375 0.0010 1.0000
12.000 1.4371 0.03241 0.02886 -0.0361 0.0010 1.0000
12.250 1.4412 0.03495 0.03164 -0.0345 0.0010 1.0000
12.500 1.4389 0.03777 0.03469 -0.0326 0.0010 1.0000
12.750 1.4278 0.04076 0.03788 -0.0304 0.0010 1.0000
13.000 1.4124 0.04499 0.04232 -0.0307 0.0010 1.0000
13.250 1.3953 0.05113 0.04866 -0.0343 0.0010 1.0000
13.500 1.3753 0.06000 0.05774 -0.0416 0.0010 1.0000
13.750 1.3480 0.07215 0.07009 -0.0509 0.0010 1.0000
14.000 1.3151 0.08466 0.08273 -0.0583 0.0010 1.0000
14.250 1.2810 0.09643 0.09459 -0.0643 0.0010 1.0000
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Polar data table (+)
Polar graphs
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