AG16 (ag16-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG16 (ag16-il) Reynolds number: 100,000 Max Cl/Cd: 48.38 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag16-il-100000-n5.txt Download as CSV file: xf-ag16-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG16
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5533 0.09086 0.08611 0.0013 1.0000 0.0231
-8.000 -0.5515 0.08637 0.08168 -0.0014 1.0000 0.0229
-7.750 -0.5495 0.08172 0.07709 -0.0047 1.0000 0.0225
-7.500 -0.5440 0.07625 0.07166 -0.0100 1.0000 0.0221
-7.250 -0.5356 0.06977 0.06519 -0.0172 1.0000 0.0217
-7.000 -0.5236 0.06179 0.05715 -0.0261 1.0000 0.0212
-6.750 -0.5099 0.05302 0.04818 -0.0346 1.0000 0.0207
-6.500 -0.4941 0.04515 0.03990 -0.0409 1.0000 0.0203
-6.250 -0.4748 0.03856 0.03273 -0.0450 1.0000 0.0201
-6.000 -0.4524 0.03336 0.02687 -0.0471 1.0000 0.0202
-5.750 -0.4280 0.02933 0.02220 -0.0481 1.0000 0.0205
-5.500 -0.4025 0.02618 0.01848 -0.0485 1.0000 0.0212
-5.250 -0.3764 0.02369 0.01547 -0.0484 1.0000 0.0223
-5.000 -0.3502 0.02189 0.01331 -0.0481 1.0000 0.0250
-4.750 -0.3250 0.02028 0.01160 -0.0480 1.0000 0.0286
-4.500 -0.2989 0.01882 0.00997 -0.0476 1.0000 0.0317
-4.250 -0.2729 0.01753 0.00852 -0.0472 1.0000 0.0368
-4.000 -0.2467 0.01660 0.00750 -0.0469 1.0000 0.0479
-3.750 -0.2205 0.01549 0.00644 -0.0468 1.0000 0.0682
-3.500 -0.1942 0.01455 0.00563 -0.0467 1.0000 0.1105
-3.250 -0.1683 0.01380 0.00516 -0.0467 1.0000 0.1738
-3.000 -0.1425 0.01327 0.00483 -0.0465 1.0000 0.2397
-2.750 -0.1168 0.01287 0.00456 -0.0463 1.0000 0.2959
-2.500 -0.0912 0.01254 0.00435 -0.0459 1.0000 0.3502
-2.250 -0.0659 0.01224 0.00415 -0.0455 1.0000 0.4043
-2.000 -0.0406 0.01198 0.00402 -0.0450 1.0000 0.4578
-1.750 -0.0154 0.01173 0.00392 -0.0446 1.0000 0.5128
-1.500 0.0098 0.01149 0.00385 -0.0440 1.0000 0.5712
-1.250 0.0343 0.01124 0.00377 -0.0433 1.0000 0.6374
-1.000 0.0621 0.01091 0.00373 -0.0431 0.9951 0.7261
-0.750 0.1023 0.01034 0.00356 -0.0447 0.9782 1.0000
-0.500 0.1435 0.01040 0.00346 -0.0475 0.9616 1.0000
-0.250 0.1833 0.01045 0.00336 -0.0499 0.9432 1.0000
0.000 0.2204 0.01049 0.00330 -0.0516 0.9219 1.0000
0.250 0.2559 0.01053 0.00325 -0.0528 0.8988 1.0000
0.500 0.2880 0.01058 0.00321 -0.0533 0.8726 1.0000
1.000 0.3457 0.01075 0.00317 -0.0526 0.8143 1.0000
1.250 0.3726 0.01087 0.00318 -0.0518 0.7833 1.0000
1.500 0.3990 0.01102 0.00323 -0.0510 0.7519 1.0000
1.750 0.4254 0.01120 0.00329 -0.0502 0.7204 1.0000
2.000 0.4518 0.01140 0.00337 -0.0495 0.6878 1.0000
2.250 0.4780 0.01162 0.00348 -0.0488 0.6553 1.0000
2.500 0.5041 0.01187 0.00362 -0.0481 0.6229 1.0000
2.750 0.5302 0.01214 0.00383 -0.0475 0.5896 1.0000
3.000 0.5561 0.01243 0.00402 -0.0469 0.5564 1.0000
3.250 0.5822 0.01274 0.00424 -0.0463 0.5228 1.0000
3.500 0.6081 0.01308 0.00449 -0.0458 0.4890 1.0000
3.750 0.6339 0.01345 0.00482 -0.0452 0.4549 1.0000
4.000 0.6597 0.01384 0.00514 -0.0447 0.4203 1.0000
4.250 0.6853 0.01426 0.00549 -0.0443 0.3857 1.0000
4.500 0.7108 0.01473 0.00588 -0.0438 0.3509 1.0000
4.750 0.7363 0.01522 0.00632 -0.0434 0.3159 1.0000
5.000 0.7614 0.01577 0.00685 -0.0430 0.2815 1.0000
5.250 0.7865 0.01635 0.00739 -0.0426 0.2476 1.0000
5.500 0.8113 0.01700 0.00798 -0.0422 0.2143 1.0000
5.750 0.8359 0.01770 0.00863 -0.0418 0.1824 1.0000
6.000 0.8603 0.01846 0.00937 -0.0414 0.1510 1.0000
6.250 0.8841 0.01934 0.01019 -0.0410 0.1211 1.0000
6.500 0.9075 0.02033 0.01122 -0.0405 0.0956 1.0000
6.750 0.9302 0.02147 0.01234 -0.0400 0.0739 1.0000
7.000 0.9524 0.02272 0.01360 -0.0394 0.0570 1.0000
7.250 0.9737 0.02415 0.01513 -0.0386 0.0457 1.0000
7.500 0.9942 0.02571 0.01682 -0.0377 0.0369 1.0000
7.750 1.0125 0.02760 0.01875 -0.0368 0.0309 1.0000
8.000 1.0328 0.02934 0.02080 -0.0357 0.0266 1.0000
8.250 1.0515 0.03097 0.02255 -0.0350 0.0224 1.0000
8.500 1.0671 0.03370 0.02558 -0.0337 0.0205 1.0000
8.750 1.0838 0.03643 0.02870 -0.0324 0.0192 1.0000
9.000 1.0980 0.03947 0.03215 -0.0311 0.0179 1.0000
9.250 1.1099 0.04231 0.03538 -0.0300 0.0165 1.0000
9.500 1.1198 0.04473 0.03808 -0.0291 0.0151 1.0000
9.750 1.1257 0.04745 0.04101 -0.0282 0.0141 1.0000
10.000 1.1229 0.05149 0.04536 -0.0272 0.0135 1.0000
10.250 1.1137 0.05583 0.05001 -0.0261 0.0133 1.0000
10.500 1.1011 0.05980 0.05428 -0.0255 0.0132 1.0000
10.750 1.0859 0.06451 0.05925 -0.0267 0.0132 1.0000
11.000 1.0696 0.07025 0.06522 -0.0300 0.0133 1.0000
11.250 1.0528 0.07711 0.07227 -0.0350 0.0133 1.0000
11.500 1.0375 0.08479 0.08018 -0.0411 0.0135 1.0000
11.750 0.9673 0.11148 0.10724 -0.0598 0.0175 1.0000
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Polar data table (+)
Polar graphs
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