AUGUST 160 (august160-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AUGUST 160 (august160-il) Reynolds number: 50,000 Max Cl/Cd: 17.34 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-august160-il-50000-n5.txt Download as CSV file: xf-august160-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AUGUST 160
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1779 0.11340 0.10669 -0.0349 0.6978 0.1201
-9.750 -0.1806 0.11096 0.10417 -0.0374 0.6833 0.1232
-9.500 -0.1868 0.10820 0.10142 -0.0404 0.6708 0.1241
-9.000 -0.1692 0.09560 0.08857 -0.0454 0.6499 0.0645
-8.750 -0.1770 0.09032 0.08325 -0.0496 0.6438 0.0587
-8.500 -0.1711 0.08711 0.08003 -0.0507 0.6320 0.0579
-8.250 -0.1690 0.08357 0.07643 -0.0525 0.6235 0.0568
-7.750 -0.1980 0.07326 0.06606 -0.0592 0.6124 0.0522
-7.500 -0.1973 0.07015 0.06283 -0.0594 0.6052 0.0519
-7.250 -0.1996 0.06660 0.05918 -0.0598 0.5976 0.0519
-7.000 -0.1975 0.06349 0.05591 -0.0596 0.5903 0.0516
-6.750 -0.1951 0.06029 0.05247 -0.0592 0.5840 0.0514
-6.500 -0.1912 0.05708 0.04904 -0.0586 0.5765 0.0514
-6.250 -0.1839 0.05416 0.04583 -0.0576 0.5699 0.0511
-6.000 -0.1746 0.05134 0.04267 -0.0565 0.5637 0.0508
-5.750 -0.1633 0.04865 0.03967 -0.0553 0.5563 0.0505
-5.500 -0.1497 0.04616 0.03679 -0.0540 0.5499 0.0502
-5.250 -0.1341 0.04378 0.03397 -0.0526 0.5442 0.0502
-5.000 -0.1163 0.04167 0.03147 -0.0513 0.5371 0.0503
-4.750 -0.0963 0.03966 0.02900 -0.0501 0.5310 0.0507
-4.500 -0.0740 0.03794 0.02681 -0.0490 0.5255 0.0512
-4.250 -0.0506 0.03644 0.02495 -0.0480 0.5184 0.0521
-4.000 -0.0264 0.03534 0.02371 -0.0473 0.5123 0.0543
-3.750 -0.0004 0.03430 0.02235 -0.0466 0.5075 0.0569
-3.500 0.0254 0.03342 0.02132 -0.0461 0.5008 0.0598
-3.250 0.0522 0.03261 0.02043 -0.0456 0.4950 0.0626
-3.000 0.0815 0.03179 0.01932 -0.0452 0.4903 0.0662
-2.750 0.1083 0.03126 0.01877 -0.0449 0.4851 0.0713
-2.500 0.1337 0.03089 0.01839 -0.0445 0.4793 0.0794
-2.250 0.1593 0.03045 0.01785 -0.0438 0.4746 0.0930
-2.000 0.1838 0.02977 0.01727 -0.0432 0.4710 0.1216
-1.750 0.2023 0.02869 0.01695 -0.0420 0.4675 0.2370
-1.500 0.3825 0.02728 0.01731 -0.0658 0.4565 0.9993
-1.250 0.4033 0.02752 0.01721 -0.0648 0.4531 1.0000
-1.000 0.4235 0.02775 0.01710 -0.0636 0.4503 1.0000
-0.750 0.4400 0.02840 0.01767 -0.0624 0.4460 1.0000
-0.500 0.4571 0.02902 0.01817 -0.0612 0.4422 1.0000
-0.250 0.4750 0.02959 0.01858 -0.0599 0.4389 1.0000
0.000 0.4935 0.03010 0.01892 -0.0587 0.4361 1.0000
0.250 0.5127 0.03059 0.01921 -0.0574 0.4338 1.0000
0.500 0.5328 0.03103 0.01944 -0.0562 0.4317 1.0000
0.750 0.5466 0.03205 0.02043 -0.0547 0.4285 1.0000
1.000 0.5584 0.03321 0.02161 -0.0531 0.4248 1.0000
1.250 0.5719 0.03418 0.02252 -0.0514 0.4214 1.0000
1.500 0.5871 0.03500 0.02326 -0.0499 0.4185 1.0000
1.750 0.6039 0.03570 0.02384 -0.0484 0.4161 1.0000
2.000 0.6220 0.03634 0.02433 -0.0471 0.4141 1.0000
2.250 0.6411 0.03697 0.02481 -0.0458 0.4125 1.0000
2.500 0.6346 0.03958 0.02762 -0.0431 0.4089 1.0000
2.750 0.6274 0.04220 0.03035 -0.0404 0.4055 1.0000
3.000 0.6238 0.04449 0.03268 -0.0379 0.4023 1.0000
3.250 0.6266 0.04626 0.03441 -0.0359 0.3997 1.0000
3.500 0.6373 0.04746 0.03554 -0.0342 0.3975 1.0000
3.750 0.6540 0.04827 0.03623 -0.0328 0.3958 1.0000
4.000 0.6734 0.04893 0.03678 -0.0317 0.3943 1.0000
4.500 0.5276 0.06518 0.05341 -0.0262 0.3812 1.0000
4.750 0.5402 0.06662 0.05476 -0.0254 0.3791 1.0000
5.000 0.5565 0.06782 0.05587 -0.0246 0.3775 1.0000
5.250 0.5737 0.06905 0.05701 -0.0238 0.3762 1.0000
5.500 0.5251 0.07619 0.06424 -0.0244 0.3712 1.0000
5.750 0.5210 0.07925 0.06728 -0.0243 0.3679 1.0000
6.000 0.5256 0.08162 0.06961 -0.0240 0.3654 1.0000
6.250 0.5335 0.08380 0.07175 -0.0238 0.3634 1.0000
6.500 0.5434 0.08587 0.07379 -0.0235 0.3619 1.0000
6.750 0.5553 0.08785 0.07572 -0.0233 0.3605 1.0000
7.000 0.5737 0.08930 0.07712 -0.0228 0.3590 1.0000
7.250 0.5648 0.09295 0.08078 -0.0232 0.3561 1.0000
7.500 0.5569 0.09640 0.08426 -0.0236 0.3529 1.0000
7.750 0.5585 0.09921 0.08708 -0.0238 0.3507 1.0000
8.000 0.5630 0.10187 0.08974 -0.0240 0.3491 1.0000
8.250 0.5702 0.10427 0.09214 -0.0241 0.3472 1.0000
8.500 0.5823 0.10629 0.09415 -0.0240 0.3451 1.0000
8.750 0.6004 0.10790 0.09573 -0.0237 0.3429 1.0000
9.000 0.6225 0.10936 0.09717 -0.0234 0.3413 1.0000
9.250 0.6037 0.11348 0.10135 -0.0243 0.3377 1.0000
9.500 0.6027 0.11623 0.10413 -0.0247 0.3341 1.0000
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Polar data table (+)
Polar graphs
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