AG35 (ag35-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG35 (ag35-il) Reynolds number: 100,000 Max Cl/Cd: 50.48 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag35-il-100000.txt Download as CSV file: xf-ag35-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG35
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3782 0.10375 0.09911 -0.0110 1.0000 0.0941
-10.750 -0.3839 0.10043 0.09583 -0.0132 1.0000 0.0977
-10.500 -0.4920 0.10628 0.10143 -0.0040 1.0000 0.0894
-10.250 -0.4848 0.10288 0.09805 -0.0045 1.0000 0.0927
-10.000 -0.4846 0.09948 0.09471 -0.0073 1.0000 0.0967
-9.750 -0.5013 0.09646 0.09182 -0.0165 1.0000 0.0992
-9.500 -0.4991 0.09125 0.08666 -0.0193 1.0000 0.1008
-9.250 -0.4790 0.08816 0.08355 -0.0129 1.0000 0.1047
-9.000 -0.4756 0.08460 0.08001 -0.0157 1.0000 0.1093
-8.750 -0.4836 0.07848 0.07386 -0.0314 1.0000 0.1145
-8.500 -0.4663 0.07602 0.07150 -0.0231 1.0000 0.1186
-8.250 -0.4670 0.07092 0.06616 -0.0362 1.0000 0.1285
-8.000 -0.4502 0.06825 0.06372 -0.0282 1.0000 0.1334
-7.750 -0.4436 0.06365 0.05900 -0.0338 1.0000 0.1443
-7.500 -0.4311 0.06088 0.05616 -0.0347 1.0000 0.1557
-7.250 -0.4206 0.05714 0.05248 -0.0334 1.0000 0.1610
-7.000 -0.4099 0.05383 0.04907 -0.0344 1.0000 0.1740
-6.750 -0.3981 0.05092 0.04608 -0.0345 1.0000 0.1881
-6.500 -0.3673 0.03654 0.03023 -0.0412 1.0000 0.0898
-6.250 -0.3435 0.03169 0.02410 -0.0400 1.0000 0.0724
-6.000 -0.3244 0.02830 0.02041 -0.0392 1.0000 0.0736
-5.750 -0.3028 0.02596 0.01773 -0.0382 1.0000 0.0741
-5.500 -0.2797 0.02389 0.01530 -0.0371 1.0000 0.0744
-5.250 -0.2564 0.02221 0.01341 -0.0362 1.0000 0.0765
-5.000 -0.2330 0.02111 0.01215 -0.0353 1.0000 0.0826
-4.750 -0.2081 0.01971 0.01057 -0.0345 1.0000 0.0878
-4.500 -0.1837 0.01865 0.00952 -0.0339 1.0000 0.0961
-4.250 -0.1590 0.01770 0.00861 -0.0334 1.0000 0.1105
-4.000 -0.1336 0.01670 0.00777 -0.0331 1.0000 0.1335
-3.750 -0.1062 0.01542 0.00702 -0.0333 1.0000 0.2121
-3.500 -0.0803 0.01326 0.00681 -0.0331 1.0000 0.6051
-3.250 -0.0568 0.01253 0.00682 -0.0307 1.0000 1.0000
-3.000 -0.0351 0.01276 0.00678 -0.0303 1.0000 1.0000
-2.750 -0.0025 0.01305 0.00680 -0.0320 0.9963 1.0000
-2.500 0.0538 0.01330 0.00676 -0.0381 0.9844 1.0000
-2.250 0.1092 0.01346 0.00671 -0.0439 0.9711 1.0000
-2.000 0.1644 0.01353 0.00661 -0.0495 0.9571 1.0000
-1.750 0.2189 0.01350 0.00646 -0.0548 0.9426 1.0000
-1.500 0.2687 0.01341 0.00628 -0.0588 0.9269 1.0000
-1.250 0.3085 0.01334 0.00613 -0.0607 0.9067 1.0000
-1.000 0.3442 0.01326 0.00597 -0.0615 0.8863 1.0000
-0.750 0.3751 0.01320 0.00583 -0.0613 0.8658 1.0000
-0.500 0.4012 0.01321 0.00577 -0.0602 0.8429 1.0000
-0.250 0.4269 0.01322 0.00569 -0.0590 0.8223 1.0000
0.000 0.4515 0.01330 0.00569 -0.0577 0.8007 1.0000
0.250 0.4765 0.01338 0.00567 -0.0564 0.7814 1.0000
0.500 0.5010 0.01354 0.00575 -0.0553 0.7601 1.0000
0.750 0.5260 0.01368 0.00582 -0.0542 0.7403 1.0000
1.000 0.5512 0.01383 0.00588 -0.0532 0.7218 1.0000
1.250 0.5763 0.01403 0.00606 -0.0524 0.7012 1.0000
1.500 0.6017 0.01420 0.00618 -0.0516 0.6818 1.0000
1.750 0.6273 0.01435 0.00627 -0.0507 0.6631 1.0000
2.000 0.6526 0.01452 0.00643 -0.0500 0.6424 1.0000
2.250 0.6782 0.01472 0.00656 -0.0491 0.6234 1.0000
2.500 0.7036 0.01505 0.00682 -0.0484 0.6029 1.0000
2.750 0.7288 0.01544 0.00715 -0.0477 0.5815 1.0000
3.000 0.7540 0.01588 0.00755 -0.0470 0.5599 1.0000
3.250 0.7788 0.01629 0.00795 -0.0463 0.5368 1.0000
3.500 0.8034 0.01668 0.00834 -0.0456 0.5129 1.0000
3.750 0.8280 0.01702 0.00863 -0.0448 0.4889 1.0000
4.000 0.8519 0.01729 0.00898 -0.0439 0.4615 1.0000
4.250 0.8758 0.01754 0.00924 -0.0431 0.4332 1.0000
4.500 0.8992 0.01784 0.00951 -0.0422 0.4038 1.0000
4.750 0.9222 0.01827 0.00985 -0.0414 0.3736 1.0000
5.000 0.9447 0.01881 0.01039 -0.0405 0.3420 1.0000
5.250 0.9668 0.01947 0.01098 -0.0397 0.3112 1.0000
5.500 0.9884 0.02025 0.01169 -0.0388 0.2816 1.0000
5.750 1.0093 0.02111 0.01248 -0.0380 0.2527 1.0000
6.000 1.0297 0.02207 0.01337 -0.0371 0.2248 1.0000
6.250 1.0492 0.02312 0.01439 -0.0361 0.1979 1.0000
6.500 1.0679 0.02426 0.01545 -0.0351 0.1721 1.0000
6.750 1.0854 0.02548 0.01657 -0.0340 0.1474 1.0000
7.000 1.1021 0.02677 0.01792 -0.0327 0.1235 1.0000
7.250 1.1179 0.02843 0.01955 -0.0314 0.1034 1.0000
7.500 1.1336 0.03021 0.02139 -0.0300 0.0872 1.0000
7.750 1.1494 0.03217 0.02339 -0.0287 0.0750 1.0000
8.000 1.1668 0.03465 0.02587 -0.0276 0.0669 1.0000
8.250 1.1825 0.03651 0.02787 -0.0263 0.0600 1.0000
8.500 1.1987 0.03959 0.03115 -0.0252 0.0556 1.0000
8.750 1.2121 0.04253 0.03450 -0.0236 0.0527 1.0000
9.000 1.2234 0.04520 0.03743 -0.0222 0.0499 1.0000
9.250 1.2350 0.04872 0.04099 -0.0214 0.0471 1.0000
9.500 1.2332 0.05228 0.04502 -0.0191 0.0459 1.0000
9.750 1.2271 0.05570 0.04890 -0.0166 0.0453 1.0000
10.000 1.2154 0.05935 0.05291 -0.0140 0.0451 1.0000
10.250 1.1991 0.06309 0.05696 -0.0118 0.0451 1.0000
10.500 1.1805 0.06728 0.06143 -0.0107 0.0451 1.0000
10.750 1.1603 0.07205 0.06643 -0.0109 0.0453 1.0000
11.000 1.1389 0.07747 0.07207 -0.0123 0.0455 1.0000
11.250 1.1167 0.08363 0.07842 -0.0148 0.0458 1.0000
11.500 1.0943 0.09058 0.08552 -0.0184 0.0462 1.0000
11.750 1.0724 0.09820 0.09326 -0.0225 0.0465 1.0000
12.000 0.9687 0.12811 0.12344 -0.0444 0.0567 1.0000
12.250 0.9591 0.13593 0.13123 -0.0473 0.0574 1.0000
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Polar data table (+)
Polar graphs
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