AUGUST 160 (august160-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AUGUST 160 (august160-il) Reynolds number: 200,000 Max Cl/Cd: 42.45 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-august160-il-200000.txt Download as CSV file: xf-august160-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1356 0.09379 0.08882 -0.0505 0.5676 0.0487
-9.250 -0.1328 0.09075 0.08578 -0.0518 0.5598 0.0502
-9.000 -0.1480 0.08619 0.08127 -0.0569 0.5565 0.0520
-8.750 -0.1582 0.08132 0.07645 -0.0604 0.5522 0.0526
-8.500 -0.1396 0.07989 0.07492 -0.0577 0.5418 0.0535
-8.250 -0.1350 0.07723 0.07227 -0.0581 0.5344 0.0542
-8.000 -0.1353 0.07421 0.06920 -0.0593 0.5287 0.0557
-7.750 -0.1471 0.07022 0.06523 -0.0622 0.5249 0.0571
-7.500 -0.1638 0.06660 0.06160 -0.0632 0.5211 0.0579
-7.250 -0.1919 0.06089 0.05568 -0.0648 0.5203 0.0597
-7.000 -0.1777 0.05894 0.05374 -0.0637 0.5129 0.0604
-6.750 -0.1676 0.05702 0.05171 -0.0628 0.5071 0.0618
-6.500 -0.1849 0.05264 0.04683 -0.0618 0.5051 0.0671
-6.250 -0.1651 0.05036 0.04470 -0.0613 0.4977 0.0681
-6.000 -0.1503 0.04862 0.04290 -0.0603 0.4918 0.0700
-5.750 -0.1461 0.04571 0.03959 -0.0588 0.4878 0.0762
-5.500 -0.1277 0.04417 0.03813 -0.0579 0.4813 0.0790
-5.250 -0.1171 0.04179 0.03548 -0.0564 0.4765 0.0857
-5.000 -0.1048 0.04018 0.03347 -0.0545 0.4721 0.0939
-4.750 -0.0846 0.03823 0.03156 -0.0539 0.4670 0.0962
-4.500 -0.0690 0.03652 0.02961 -0.0523 0.4623 0.1047
-4.250 -0.0512 0.02678 0.01820 -0.0464 0.4609 0.0445
-4.000 -0.0276 0.02469 0.01545 -0.0444 0.4564 0.0402
-3.750 -0.0019 0.02342 0.01398 -0.0436 0.4522 0.0397
-3.500 0.0243 0.02240 0.01277 -0.0428 0.4480 0.0395
-3.250 0.0508 0.02150 0.01174 -0.0421 0.4434 0.0397
-3.000 0.0776 0.02084 0.01091 -0.0414 0.4391 0.0404
-2.750 0.1035 0.02013 0.01023 -0.0409 0.4354 0.0426
-2.500 0.1297 0.01972 0.00972 -0.0403 0.4319 0.0441
-2.250 0.1550 0.01927 0.00927 -0.0395 0.4284 0.0455
-2.000 0.1790 0.01877 0.00882 -0.0385 0.4248 0.0469
-1.750 0.2029 0.01839 0.00848 -0.0375 0.4213 0.0496
-1.500 0.2270 0.01805 0.00810 -0.0366 0.4180 0.0540
-1.250 0.2511 0.01774 0.00774 -0.0356 0.4150 0.0639
-0.750 0.3081 0.01506 0.00822 -0.0347 0.4089 0.9021
-0.500 0.4669 0.01609 0.00886 -0.0582 0.4020 0.9850
-0.250 0.5323 0.01610 0.00862 -0.0657 0.3985 0.9972
0.000 0.5653 0.01623 0.00857 -0.0670 0.3960 1.0000
0.250 0.5874 0.01655 0.00877 -0.0661 0.3939 1.0000
0.500 0.6088 0.01670 0.00891 -0.0651 0.3919 1.0000
0.750 0.6303 0.01689 0.00910 -0.0640 0.3897 1.0000
1.000 0.6521 0.01711 0.00929 -0.0631 0.3876 1.0000
1.250 0.6739 0.01734 0.00948 -0.0621 0.3854 1.0000
1.500 0.6959 0.01758 0.00967 -0.0611 0.3834 1.0000
1.750 0.7181 0.01783 0.00986 -0.0602 0.3817 1.0000
2.000 0.7406 0.01807 0.01002 -0.0593 0.3799 1.0000
2.250 0.7633 0.01838 0.01023 -0.0585 0.3780 1.0000
2.500 0.7855 0.01896 0.01073 -0.0577 0.3761 1.0000
2.750 0.8057 0.01931 0.01114 -0.0564 0.3748 1.0000
3.000 0.8256 0.01972 0.01160 -0.0552 0.3732 1.0000
3.250 0.8455 0.02016 0.01209 -0.0540 0.3716 1.0000
3.500 0.8653 0.02063 0.01260 -0.0527 0.3699 1.0000
3.750 0.8851 0.02108 0.01307 -0.0515 0.3682 1.0000
4.000 0.9051 0.02150 0.01351 -0.0503 0.3665 1.0000
4.250 0.9254 0.02188 0.01389 -0.0491 0.3648 1.0000
4.500 0.9458 0.02230 0.01431 -0.0480 0.3633 1.0000
4.750 0.9662 0.02276 0.01476 -0.0469 0.3621 1.0000
5.000 0.9870 0.02325 0.01522 -0.0458 0.3609 1.0000
5.250 1.0082 0.02382 0.01576 -0.0449 0.3596 1.0000
5.500 1.0268 0.02471 0.01666 -0.0437 0.3581 1.0000
5.750 1.0398 0.02540 0.01750 -0.0416 0.3567 1.0000
6.000 1.0521 0.02625 0.01849 -0.0395 0.3552 1.0000
6.250 1.0637 0.02721 0.01957 -0.0373 0.3537 1.0000
6.500 1.0751 0.02820 0.02067 -0.0352 0.3521 1.0000
6.750 1.0868 0.02921 0.02179 -0.0332 0.3506 1.0000
7.000 1.0993 0.03018 0.02284 -0.0313 0.3492 1.0000
7.250 1.1128 0.03111 0.02384 -0.0296 0.3479 1.0000
7.500 1.1278 0.03199 0.02476 -0.0282 0.3467 1.0000
7.750 1.1433 0.03283 0.02565 -0.0268 0.3455 1.0000
8.000 1.1603 0.03361 0.02646 -0.0257 0.3444 1.0000
8.250 1.1786 0.03441 0.02727 -0.0247 0.3433 1.0000
8.500 1.2009 0.03511 0.02796 -0.0242 0.3422 1.0000
8.750 1.1991 0.03726 0.03025 -0.0214 0.3405 1.0000
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Polar data table (+)
Polar graphs
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