AG17 (ag17-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG17 (ag17-il) Reynolds number: 100,000 Max Cl/Cd: 49.55 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag17-il-100000.txt Download as CSV file: xf-ag17-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG17
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4342 0.10077 0.09621 0.0020 1.0000 0.0855
-8.500 -0.4442 0.09791 0.09342 -0.0018 1.0000 0.0879
-8.250 -0.4570 0.09519 0.09079 -0.0066 1.0000 0.0886
-8.000 -0.4337 0.08887 0.08444 -0.0019 1.0000 0.0919
-7.750 -0.4279 0.08514 0.08074 -0.0020 1.0000 0.0958
-7.500 -0.4313 0.08157 0.07722 -0.0044 1.0000 0.0998
-7.250 -0.4476 0.07814 0.07390 -0.0136 1.0000 0.1019
-7.000 -0.5110 0.08527 0.08076 -0.0015 1.0000 0.0963
-6.750 -0.4984 0.07886 0.07431 -0.0218 1.0000 0.1027
-6.500 -0.4896 0.07586 0.07140 -0.0132 1.0000 0.1054
-6.250 -0.4733 0.07163 0.06714 -0.0189 1.0000 0.1137
-6.000 -0.4589 0.06667 0.06217 -0.0227 1.0000 0.1188
-5.750 -0.4377 0.06133 0.05667 -0.0313 1.0000 0.1306
-5.500 -0.4232 0.05837 0.05380 -0.0287 1.0000 0.1353
-5.250 -0.4021 0.05386 0.04918 -0.0331 1.0000 0.1471
-5.000 -0.3527 0.03812 0.03207 -0.0485 1.0000 0.0772
-4.750 -0.3227 0.03171 0.02500 -0.0499 1.0000 0.0582
-4.500 -0.2936 0.02706 0.01960 -0.0507 1.0000 0.0534
-4.250 -0.2663 0.02466 0.01680 -0.0507 1.0000 0.0571
-4.000 -0.2377 0.02229 0.01383 -0.0504 1.0000 0.0600
-3.750 -0.2092 0.02025 0.01130 -0.0497 1.0000 0.0622
-3.500 -0.1828 0.01809 0.00916 -0.0493 1.0000 0.0704
-3.250 -0.1560 0.01668 0.00767 -0.0488 1.0000 0.0876
-3.000 -0.1296 0.01511 0.00635 -0.0484 1.0000 0.1253
-2.750 -0.1032 0.01348 0.00534 -0.0483 1.0000 0.2332
-2.500 -0.0781 0.01247 0.00499 -0.0479 1.0000 0.3851
-2.250 -0.0543 0.01184 0.00474 -0.0470 1.0000 0.5049
-2.000 -0.0314 0.01123 0.00453 -0.0455 1.0000 0.6231
-1.750 -0.0147 0.01039 0.00430 -0.0420 1.0000 0.7915
-1.500 0.0142 0.00999 0.00389 -0.0418 1.0000 1.0000
-1.250 0.0412 0.01004 0.00365 -0.0420 1.0000 1.0000
-1.000 0.0676 0.01012 0.00351 -0.0420 1.0000 1.0000
-0.750 0.0935 0.01022 0.00345 -0.0419 1.0000 1.0000
-0.500 0.1192 0.01035 0.00345 -0.0419 1.0000 1.0000
-0.250 0.1447 0.01051 0.00351 -0.0419 1.0000 1.0000
0.000 0.1699 0.01072 0.00361 -0.0420 1.0000 1.0000
0.250 0.1947 0.01098 0.00381 -0.0422 1.0000 1.0000
0.500 0.2190 0.01130 0.00409 -0.0425 1.0000 1.0000
0.750 0.2569 0.01165 0.00442 -0.0455 0.9931 1.0000
1.000 0.3158 0.01181 0.00460 -0.0520 0.9722 1.0000
1.250 0.3725 0.01184 0.00467 -0.0575 0.9511 1.0000
1.500 0.4208 0.01177 0.00466 -0.0609 0.9269 1.0000
1.750 0.4577 0.01172 0.00467 -0.0617 0.8969 1.0000
2.000 0.4874 0.01171 0.00466 -0.0609 0.8637 1.0000
2.250 0.5132 0.01175 0.00466 -0.0591 0.8292 1.0000
2.500 0.5369 0.01185 0.00470 -0.0571 0.7918 1.0000
2.750 0.5602 0.01202 0.00483 -0.0551 0.7522 1.0000
3.000 0.5837 0.01224 0.00494 -0.0533 0.7108 1.0000
3.250 0.6073 0.01253 0.00509 -0.0516 0.6679 1.0000
3.500 0.6312 0.01286 0.00528 -0.0501 0.6230 1.0000
3.750 0.6553 0.01325 0.00552 -0.0488 0.5758 1.0000
4.000 0.6793 0.01371 0.00585 -0.0476 0.5294 1.0000
4.250 0.7036 0.01422 0.00621 -0.0465 0.4810 1.0000
4.500 0.7277 0.01480 0.00661 -0.0456 0.4345 1.0000
4.750 0.7518 0.01544 0.00709 -0.0447 0.3887 1.0000
5.000 0.7759 0.01614 0.00765 -0.0440 0.3439 1.0000
5.250 0.7998 0.01691 0.00834 -0.0432 0.3012 1.0000
5.500 0.8236 0.01776 0.00907 -0.0426 0.2602 1.0000
5.750 0.8471 0.01873 0.00992 -0.0419 0.2216 1.0000
6.000 0.8702 0.01981 0.01083 -0.0412 0.1857 1.0000
6.250 0.8935 0.02107 0.01206 -0.0404 0.1535 1.0000
6.500 0.9162 0.02235 0.01329 -0.0397 0.1250 1.0000
6.750 0.9389 0.02412 0.01510 -0.0388 0.1034 1.0000
7.000 0.9613 0.02574 0.01675 -0.0380 0.0845 1.0000
7.250 0.9839 0.02789 0.01898 -0.0370 0.0710 1.0000
7.500 1.0060 0.03030 0.02167 -0.0360 0.0605 1.0000
7.750 1.0266 0.03361 0.02526 -0.0349 0.0539 1.0000
8.000 1.0463 0.03574 0.02769 -0.0339 0.0470 1.0000
8.500 1.0727 0.04538 0.03834 -0.0315 0.0437 1.0000
8.750 1.0793 0.05023 0.04385 -0.0301 0.0433 1.0000
9.000 1.0805 0.05527 0.04947 -0.0290 0.0428 1.0000
9.250 1.0758 0.06053 0.05521 -0.0284 0.0425 1.0000
9.500 1.0660 0.06590 0.06095 -0.0282 0.0426 1.0000
9.750 1.0519 0.07121 0.06651 -0.0286 0.0429 1.0000
10.000 1.0349 0.07628 0.07172 -0.0292 0.0434 1.0000
10.250 1.0194 0.08206 0.07757 -0.0314 0.0440 1.0000
10.500 0.9583 0.10290 0.09868 -0.0520 0.0540 1.0000
10.750 0.9293 0.11835 0.11402 -0.0630 0.0633 1.0000
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Polar data table (+)
Polar graphs
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