AG35 (ag35-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG35 (ag35-il) Reynolds number: 50,000 Max Cl/Cd: 32.35 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag35-il-50000.txt Download as CSV file: xf-ag35-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4836 0.10209 0.09555 -0.0002 1.0000 0.2452
-9.250 -0.4785 0.09893 0.09244 -0.0002 1.0000 0.2583
-9.000 -0.4715 0.09538 0.08893 0.0003 1.0000 0.2726
-8.750 -0.4692 0.09230 0.08593 0.0005 1.0000 0.2875
-8.500 -0.4712 0.08959 0.08330 -0.0005 1.0000 0.3030
-8.000 -0.4441 0.08167 0.07545 0.0032 1.0000 0.3382
-7.750 -0.4402 0.07876 0.07261 0.0037 1.0000 0.3592
-7.500 -0.4354 0.07555 0.06945 0.0046 1.0000 0.3805
-7.250 -0.4351 0.07305 0.06704 0.0055 1.0000 0.4078
-7.000 -0.4266 0.07003 0.06408 0.0084 1.0000 0.4375
-6.750 -0.4025 0.05486 0.04813 -0.0325 1.0000 0.2138
-6.500 -0.3722 0.04451 0.03657 -0.0406 1.0000 0.1415
-6.250 -0.3528 0.04081 0.03265 -0.0403 1.0000 0.1383
-6.000 -0.3317 0.03736 0.02877 -0.0403 1.0000 0.1372
-5.750 -0.3089 0.03414 0.02502 -0.0400 1.0000 0.1358
-5.500 -0.2848 0.03130 0.02167 -0.0394 1.0000 0.1354
-5.250 -0.2601 0.02909 0.01893 -0.0387 1.0000 0.1407
-5.000 -0.2367 0.02717 0.01687 -0.0379 1.0000 0.1496
-4.750 -0.2109 0.02534 0.01469 -0.0370 1.0000 0.1589
-4.500 -0.1868 0.02391 0.01326 -0.0362 1.0000 0.1785
-4.250 -0.1613 0.02246 0.01181 -0.0352 1.0000 0.2059
-4.000 -0.1349 0.02096 0.01058 -0.0345 1.0000 0.2669
-3.750 -0.0980 0.01634 0.00926 -0.0318 1.0000 1.0000
-3.500 -0.0761 0.01642 0.00859 -0.0313 1.0000 1.0000
-3.250 -0.0555 0.01656 0.00825 -0.0305 1.0000 1.0000
-3.000 -0.0350 0.01674 0.00807 -0.0298 1.0000 1.0000
-2.750 -0.0146 0.01697 0.00800 -0.0292 1.0000 1.0000
-2.500 0.0057 0.01725 0.00803 -0.0287 1.0000 1.0000
-2.250 0.0257 0.01761 0.00815 -0.0284 1.0000 1.0000
-2.000 0.0451 0.01804 0.00841 -0.0281 1.0000 1.0000
-1.750 0.0638 0.01858 0.00879 -0.0280 1.0000 1.0000
-1.500 0.0816 0.01925 0.00932 -0.0280 1.0000 1.0000
-1.250 0.0987 0.02002 0.00996 -0.0283 1.0000 1.0000
-1.000 0.1265 0.02092 0.01074 -0.0305 0.9956 1.0000
-0.750 0.1878 0.02189 0.01157 -0.0385 0.9754 1.0000
-0.500 0.2485 0.02274 0.01232 -0.0460 0.9563 1.0000
-0.250 0.2980 0.02343 0.01297 -0.0511 0.9350 1.0000
0.000 0.3501 0.02400 0.01354 -0.0563 0.9151 1.0000
0.250 0.4052 0.02441 0.01397 -0.0616 0.8965 1.0000
0.500 0.4440 0.02487 0.01446 -0.0639 0.8752 1.0000
0.750 0.4883 0.02510 0.01476 -0.0665 0.8559 1.0000
1.000 0.5281 0.02528 0.01500 -0.0680 0.8364 1.0000
1.250 0.5599 0.02555 0.01533 -0.0681 0.8151 1.0000
1.500 0.5970 0.02549 0.01538 -0.0683 0.7960 1.0000
1.750 0.6231 0.02580 0.01576 -0.0672 0.7738 1.0000
2.000 0.6537 0.02580 0.01582 -0.0661 0.7534 1.0000
2.250 0.6790 0.02605 0.01618 -0.0646 0.7309 1.0000
2.500 0.7063 0.02606 0.01626 -0.0628 0.7092 1.0000
2.750 0.7300 0.02632 0.01660 -0.0610 0.6851 1.0000
3.000 0.7567 0.02623 0.01654 -0.0590 0.6624 1.0000
3.250 0.7813 0.02629 0.01670 -0.0569 0.6373 1.0000
3.500 0.8056 0.02646 0.01691 -0.0549 0.6110 1.0000
3.750 0.8296 0.02682 0.01729 -0.0529 0.5836 1.0000
4.000 0.8530 0.02735 0.01783 -0.0509 0.5547 1.0000
4.250 0.8759 0.02798 0.01851 -0.0490 0.5248 1.0000
4.500 0.8984 0.02863 0.01918 -0.0472 0.4945 1.0000
4.750 0.9208 0.02922 0.01980 -0.0454 0.4641 1.0000
5.000 0.9435 0.02967 0.02026 -0.0436 0.4340 1.0000
5.250 0.9662 0.03007 0.02066 -0.0419 0.4038 1.0000
5.500 0.9889 0.03057 0.02109 -0.0402 0.3738 1.0000
5.750 1.0094 0.03143 0.02197 -0.0386 0.3426 1.0000
6.000 1.0294 0.03245 0.02300 -0.0369 0.3115 1.0000
6.250 1.0489 0.03370 0.02426 -0.0353 0.2811 1.0000
6.500 1.0678 0.03520 0.02573 -0.0338 0.2519 1.0000
6.750 1.0855 0.03693 0.02745 -0.0322 0.2239 1.0000
7.000 1.1024 0.03888 0.02938 -0.0307 0.1979 1.0000
7.250 1.1210 0.04095 0.03125 -0.0294 0.1742 1.0000
7.500 1.1321 0.04384 0.03454 -0.0275 0.1562 1.0000
7.750 1.1438 0.04670 0.03768 -0.0258 0.1408 1.0000
8.000 1.1546 0.05006 0.04127 -0.0242 0.1297 1.0000
8.250 1.1678 0.05312 0.04436 -0.0230 0.1191 1.0000
8.500 1.1615 0.05788 0.04982 -0.0208 0.1160 1.0000
8.750 1.1536 0.06256 0.05496 -0.0189 0.1132 1.0000
9.000 1.1669 0.06580 0.05811 -0.0181 0.1062 1.0000
9.250 1.1490 0.07076 0.06348 -0.0164 0.1058 1.0000
9.500 1.1283 0.07573 0.06873 -0.0152 0.1059 1.0000
9.750 1.1059 0.08077 0.07394 -0.0145 0.1063 1.0000
10.000 1.0844 0.08646 0.07976 -0.0153 0.1068 1.0000
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Polar data table (+)
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