AH 85-L-120/17 (ah85l120-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 85-L-120/17 (ah85l120-il) Reynolds number: 50,000 Max Cl/Cd: 27.12 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah85l120-il-50000-n5.txt Download as CSV file: xf-ah85l120-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 85-L-120/17
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5922 0.10399 0.09698 -0.0350 1.0000 0.0441
-11.500 -0.6056 0.09587 0.08888 -0.0402 1.0000 0.0427
-11.250 -0.6261 0.08832 0.08133 -0.0451 1.0000 0.0419
-11.000 -0.6523 0.08167 0.07462 -0.0485 1.0000 0.0411
-10.750 -0.6933 0.07564 0.06835 -0.0500 1.0000 0.0395
-10.500 -0.7146 0.07216 0.06468 -0.0489 1.0000 0.0390
-10.250 -0.7302 0.06897 0.06137 -0.0469 1.0000 0.0392
-10.000 -0.7464 0.06612 0.05837 -0.0438 1.0000 0.0392
-9.750 -0.7595 0.06364 0.05565 -0.0403 1.0000 0.0388
-9.500 -0.7690 0.06062 0.05242 -0.0371 1.0000 0.0390
-9.250 -0.7768 0.05784 0.04940 -0.0335 1.0000 0.0391
-9.000 -0.7823 0.05549 0.04679 -0.0297 1.0000 0.0389
-8.750 -0.7872 0.05273 0.04379 -0.0258 1.0000 0.0393
-8.500 -0.7893 0.05036 0.04113 -0.0219 1.0000 0.0394
-8.250 -0.7887 0.04808 0.03860 -0.0183 1.0000 0.0397
-8.000 -0.7850 0.04574 0.03599 -0.0149 1.0000 0.0402
-7.750 -0.7775 0.04340 0.03336 -0.0119 1.0000 0.0411
-7.500 -0.7662 0.04134 0.03103 -0.0095 1.0000 0.0419
-7.250 -0.7533 0.03951 0.02889 -0.0072 1.0000 0.0443
-7.000 -0.7372 0.03780 0.02685 -0.0052 1.0000 0.0479
-6.750 -0.7140 0.03609 0.02472 -0.0040 1.0000 0.0505
-6.500 -0.6840 0.03403 0.02268 -0.0041 1.0000 0.0537
-6.250 -0.6602 0.03268 0.02119 -0.0031 1.0000 0.0596
-6.000 -0.6409 0.03153 0.01991 -0.0016 1.0000 0.0664
-5.750 -0.6275 0.03048 0.01873 0.0009 1.0000 0.0740
-5.500 -0.6181 0.02933 0.01751 0.0039 1.0000 0.0824
-5.250 -0.6104 0.02822 0.01645 0.0070 1.0000 0.1010
-5.000 -0.6060 0.02681 0.01536 0.0105 1.0000 0.1353
-4.750 -0.6093 0.02486 0.01427 0.0149 1.0000 0.2427
-4.500 -0.6178 0.02279 0.01381 0.0212 1.0000 0.4748
-4.250 -0.5826 0.02552 0.01742 0.0272 1.0000 0.7416
-4.000 -0.5676 0.02727 0.01892 0.0329 1.0000 0.8000
-3.750 -0.5384 0.02829 0.01954 0.0346 1.0000 0.8314
-3.500 -0.4902 0.02908 0.01990 0.0323 1.0000 0.8532
-3.250 -0.4633 0.02924 0.01977 0.0328 1.0000 0.8731
-3.000 -0.4215 0.02935 0.01956 0.0301 1.0000 0.8873
-2.750 -0.3791 0.02930 0.01917 0.0269 1.0000 0.8976
-2.500 -0.3469 0.02912 0.01876 0.0253 1.0000 0.9071
-2.250 -0.3211 0.02892 0.01838 0.0248 1.0000 0.9173
-2.000 -0.2915 0.02873 0.01798 0.0235 1.0000 0.9260
-1.750 -0.2611 0.02854 0.01764 0.0219 1.0000 0.9338
-1.500 -0.2349 0.02839 0.01737 0.0211 0.9990 0.9425
-1.250 -0.1919 0.02825 0.01710 0.0168 0.9954 0.9473
-1.000 -0.1539 0.02817 0.01688 0.0136 0.9915 0.9535
-0.750 -0.1161 0.02810 0.01673 0.0104 0.9874 0.9591
-0.500 -0.0758 0.02805 0.01662 0.0066 0.9833 0.9641
-0.250 -0.0408 0.02805 0.01658 0.0039 0.9787 0.9699
0.000 0.0001 0.02800 0.01652 0.0000 0.9739 0.9740
0.250 0.0408 0.02805 0.01658 -0.0039 0.9697 0.9786
0.500 0.0756 0.02805 0.01662 -0.0065 0.9640 0.9832
0.750 0.1162 0.02810 0.01673 -0.0103 0.9591 0.9874
1.000 0.1541 0.02817 0.01688 -0.0136 0.9535 0.9915
1.250 0.1920 0.02825 0.01709 -0.0168 0.9474 0.9955
1.500 0.2352 0.02839 0.01736 -0.0211 0.9427 0.9990
1.750 0.2605 0.02854 0.01764 -0.0218 0.9340 1.0000
2.000 0.2914 0.02873 0.01801 -0.0235 0.9262 1.0000
2.250 0.3212 0.02891 0.01837 -0.0248 0.9173 1.0000
2.500 0.3469 0.02911 0.01875 -0.0253 0.9071 1.0000
2.750 0.3793 0.02929 0.01915 -0.0269 0.8974 1.0000
3.000 0.4216 0.02935 0.01950 -0.0301 0.8873 1.0000
3.250 0.4629 0.02925 0.01978 -0.0327 0.8731 1.0000
3.500 0.4900 0.02908 0.01989 -0.0323 0.8534 1.0000
3.750 0.5380 0.02829 0.01953 -0.0346 0.8315 1.0000
4.000 0.5671 0.02726 0.01892 -0.0328 0.7996 1.0000
4.250 0.5836 0.02553 0.01743 -0.0273 0.7428 1.0000
4.500 0.6179 0.02278 0.01386 -0.0213 0.4821 1.0000
4.750 0.6097 0.02482 0.01425 -0.0150 0.2462 1.0000
5.000 0.6065 0.02675 0.01533 -0.0106 0.1378 1.0000
5.250 0.6102 0.02827 0.01648 -0.0070 0.0971 1.0000
5.500 0.6181 0.02935 0.01752 -0.0039 0.0820 1.0000
5.750 0.6277 0.03050 0.01878 -0.0008 0.0732 1.0000
6.000 0.6404 0.03159 0.01992 0.0016 0.0649 1.0000
6.250 0.6596 0.03270 0.02121 0.0032 0.0573 1.0000
6.500 0.6835 0.03402 0.02266 0.0041 0.0534 1.0000
6.750 0.7144 0.03611 0.02476 0.0039 0.0504 1.0000
7.000 0.7371 0.03785 0.02693 0.0053 0.0471 1.0000
7.250 0.7535 0.03956 0.02893 0.0072 0.0442 1.0000
7.500 0.7662 0.04134 0.03102 0.0095 0.0419 1.0000
7.750 0.7776 0.04348 0.03345 0.0120 0.0409 1.0000
8.000 0.7848 0.04579 0.03601 0.0149 0.0400 1.0000
8.250 0.7885 0.04819 0.03867 0.0182 0.0394 1.0000
8.500 0.7891 0.05050 0.04126 0.0219 0.0392 1.0000
8.750 0.7866 0.05310 0.04411 0.0257 0.0389 1.0000
9.000 0.7819 0.05571 0.04698 0.0296 0.0388 1.0000
9.250 0.7764 0.05806 0.04960 0.0334 0.0389 1.0000
9.500 0.7691 0.06067 0.05245 0.0370 0.0389 1.0000
9.750 0.7590 0.06377 0.05577 0.0403 0.0388 1.0000
10.000 0.7472 0.06681 0.05897 0.0433 0.0386 1.0000
10.250 0.7325 0.06937 0.06171 0.0464 0.0387 1.0000
10.500 0.7155 0.07248 0.06495 0.0487 0.0387 1.0000
10.750 0.6949 0.07580 0.06847 0.0500 0.0391 1.0000
11.000 0.6542 0.08152 0.07445 0.0486 0.0409 1.0000
11.250 0.6270 0.08827 0.08127 0.0452 0.0416 1.0000
11.500 0.6056 0.09605 0.08906 0.0400 0.0428 1.0000
11.750 0.5922 0.10420 0.09717 0.0348 0.0438 1.0000
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Polar data table (+)
Polar graphs
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