HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il) Reynolds number: 200,000 Max Cl/Cd: 78.6 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1404-il-200000-n5.txt Download as CSV file: xf-hs1404-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-404 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4454 0.09557 0.09204 -0.0097 1.0000 0.0135
-7.500 -0.4404 0.09242 0.08893 -0.0112 1.0000 0.0138
-7.250 -0.4353 0.08927 0.08582 -0.0129 1.0000 0.0141
-7.000 -0.4268 0.08580 0.08238 -0.0157 1.0000 0.0143
-6.750 -0.4167 0.08221 0.07883 -0.0189 1.0000 0.0146
-6.500 -0.4054 0.07851 0.07515 -0.0224 1.0000 0.0148
-5.000 -0.3007 0.05267 0.04910 -0.0457 1.0000 0.0074
-4.750 -0.2737 0.04754 0.04385 -0.0506 0.9993 0.0071
-4.500 -0.2297 0.04110 0.03718 -0.0586 0.9965 0.0070
-4.250 -0.1845 0.03449 0.03025 -0.0655 0.9943 0.0069
-4.000 -0.1415 0.02812 0.02343 -0.0705 0.9918 0.0073
-3.750 -0.1019 0.02306 0.01773 -0.0750 0.9893 0.0107
-3.500 -0.0647 0.02013 0.01428 -0.0775 0.9868 0.0123
-3.250 -0.0271 0.01716 0.01063 -0.0793 0.9848 0.0117
-3.000 0.0088 0.01519 0.00821 -0.0807 0.9831 0.0114
-2.750 0.0425 0.01378 0.00653 -0.0817 0.9803 0.0112
-2.500 0.0758 0.01275 0.00531 -0.0827 0.9768 0.0113
-2.250 0.1103 0.01201 0.00433 -0.0840 0.9738 0.0120
-2.000 0.1451 0.01147 0.00359 -0.0854 0.9712 0.0136
-1.750 0.1792 0.01079 0.00302 -0.0867 0.9682 0.0612
-1.500 0.2103 0.01033 0.00308 -0.0878 0.9632 0.1947
-1.250 0.2432 0.01019 0.00292 -0.0890 0.9591 0.2220
-1.000 0.2763 0.01002 0.00276 -0.0902 0.9554 0.2492
-0.750 0.3070 0.00984 0.00258 -0.0909 0.9485 0.2790
-0.250 0.3632 0.00793 0.00238 -0.0906 0.9325 1.0000
0.000 0.3933 0.00792 0.00228 -0.0908 0.9216 1.0000
0.250 0.4226 0.00791 0.00219 -0.0908 0.9094 1.0000
0.500 0.4508 0.00792 0.00217 -0.0906 0.8969 1.0000
0.750 0.4786 0.00796 0.00216 -0.0903 0.8862 1.0000
1.250 0.5334 0.00807 0.00225 -0.0898 0.8668 1.0000
1.500 0.5603 0.00814 0.00233 -0.0894 0.8558 1.0000
1.750 0.5871 0.00822 0.00243 -0.0890 0.8438 1.0000
2.000 0.6137 0.00830 0.00254 -0.0885 0.8300 1.0000
2.250 0.6393 0.00837 0.00271 -0.0876 0.8078 1.0000
2.500 0.6631 0.00847 0.00271 -0.0861 0.7623 1.0000
2.750 0.6854 0.00872 0.00267 -0.0842 0.6691 1.0000
3.000 0.7027 0.00979 0.00281 -0.0818 0.4883 1.0000
3.250 0.7227 0.01096 0.00328 -0.0806 0.3418 1.0000
3.500 0.7454 0.01187 0.00377 -0.0800 0.2372 1.0000
3.750 0.7656 0.01336 0.00448 -0.0793 0.0866 1.0000
4.000 0.7894 0.01423 0.00531 -0.0788 0.0506 1.0000
4.250 0.8143 0.01490 0.00606 -0.0782 0.0394 1.0000
4.500 0.8381 0.01581 0.00708 -0.0774 0.0325 1.0000
4.750 0.8625 0.01651 0.00790 -0.0768 0.0257 1.0000
5.000 0.8847 0.01780 0.00931 -0.0758 0.0214 1.0000
5.250 0.9096 0.01843 0.01006 -0.0752 0.0141 1.0000
5.750 0.9550 0.02093 0.01279 -0.0734 0.0050 1.0000
6.000 0.9768 0.02304 0.01518 -0.0720 0.0041 1.0000
6.250 0.9984 0.02599 0.01867 -0.0704 0.0035 1.0000
6.500 1.0186 0.02969 0.02293 -0.0685 0.0032 1.0000
6.750 1.0357 0.03420 0.02807 -0.0662 0.0031 1.0000
7.000 1.0485 0.03941 0.03391 -0.0636 0.0031 1.0000
7.250 1.0573 0.04501 0.04005 -0.0610 0.0032 1.0000
7.500 1.0624 0.05065 0.04615 -0.0586 0.0032 1.0000
7.750 1.0641 0.05623 0.05211 -0.0565 0.0033 1.0000
8.000 1.0620 0.06174 0.05794 -0.0547 0.0033 1.0000
8.250 1.0562 0.06711 0.06356 -0.0533 0.0034 1.0000
8.500 1.0465 0.07234 0.06899 -0.0524 0.0034 1.0000
8.750 1.0313 0.07708 0.07389 -0.0515 0.0035 1.0000
9.000 1.0149 0.08237 0.07929 -0.0527 0.0035 1.0000
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Polar data table (+)
Polar graphs
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