S4320 (s4320-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4320 (s4320-il) Reynolds number: 50,000 Max Cl/Cd: 32.32 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4320-il-50000.txt Download as CSV file: xf-s4320-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S4320
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3072 0.11196 0.10562 -0.0302 1.0000 0.1668
-8.250 -0.2788 0.10488 0.09852 -0.0280 1.0000 0.1746
-8.000 -0.2887 0.10435 0.09814 -0.0291 1.0000 0.1807
-7.750 -0.2793 0.10030 0.09417 -0.0284 1.0000 0.1857
-7.500 -0.2804 0.09845 0.09244 -0.0276 1.0000 0.1937
-7.250 -0.3060 0.09934 0.09358 -0.0262 1.0000 0.1961
-7.000 -0.2883 0.09456 0.08883 -0.0241 1.0000 0.2062
-6.750 -0.3125 0.09489 0.08936 -0.0207 1.0000 0.2093
-6.500 -0.3419 0.09568 0.09034 -0.0184 1.0000 0.2110
-6.250 -0.3343 0.09204 0.08675 -0.0143 1.0000 0.2196
-6.000 -0.3562 0.09200 0.08685 -0.0125 1.0000 0.2246
-5.750 -0.3760 0.09142 0.08641 -0.0129 1.0000 0.2274
-5.500 -0.3746 0.08887 0.08390 -0.0088 1.0000 0.2392
-5.250 -0.3792 0.08661 0.08171 -0.0068 1.0000 0.2464
-5.000 -0.3915 0.08586 0.08105 -0.0101 1.0000 0.2571
-4.750 -0.3896 0.08316 0.07838 -0.0059 1.0000 0.2697
-4.500 -0.3893 0.08058 0.07586 -0.0035 1.0000 0.2809
-4.250 -0.3895 0.07826 0.07359 -0.0027 1.0000 0.2948
-4.000 -0.3882 0.07605 0.07142 -0.0023 1.0000 0.3122
-3.750 -0.3857 0.07374 0.06913 -0.0030 1.0000 0.3334
-3.500 -0.3826 0.07126 0.06672 0.0002 1.0000 0.3525
-3.250 -0.3791 0.06901 0.06450 0.0016 1.0000 0.3801
-3.000 -0.3764 0.06678 0.06233 0.0046 1.0000 0.4104
-2.750 -0.3752 0.06471 0.06031 0.0089 1.0000 0.4458
-2.250 -0.1237 0.04244 0.03508 -0.0623 0.9946 0.1485
-2.000 -0.0671 0.03873 0.03044 -0.0686 0.9872 0.1343
-1.750 -0.0182 0.03650 0.02758 -0.0730 0.9794 0.1329
-1.500 0.0307 0.03502 0.02543 -0.0771 0.9711 0.1384
-1.250 0.0681 0.03389 0.02410 -0.0792 0.9622 0.1440
-1.000 0.1105 0.03304 0.02292 -0.0817 0.9536 0.1558
-0.750 0.1513 0.03245 0.02229 -0.0840 0.9443 0.1899
-0.500 0.1909 0.02908 0.02148 -0.0852 0.9379 0.6279
-0.250 0.2287 0.02912 0.02108 -0.0863 0.9272 1.0000
0.000 0.2592 0.02993 0.02142 -0.0877 0.9156 1.0000
0.250 0.2901 0.03080 0.02191 -0.0891 0.9042 1.0000
0.500 0.3234 0.03171 0.02251 -0.0909 0.8928 1.0000
0.750 0.3600 0.03265 0.02315 -0.0931 0.8813 1.0000
1.000 0.3958 0.03354 0.02381 -0.0950 0.8695 1.0000
1.250 0.4215 0.03444 0.02452 -0.0955 0.8568 1.0000
1.500 0.4490 0.03537 0.02530 -0.0962 0.8441 1.0000
1.750 0.4779 0.03630 0.02610 -0.0970 0.8312 1.0000
2.000 0.5076 0.03723 0.02692 -0.0979 0.8182 1.0000
2.250 0.5386 0.03812 0.02772 -0.0988 0.8050 1.0000
2.500 0.5703 0.03898 0.02851 -0.0997 0.7918 1.0000
2.750 0.6031 0.03978 0.02926 -0.1006 0.7784 1.0000
3.000 0.6371 0.04049 0.02993 -0.1015 0.7648 1.0000
3.250 0.6693 0.04117 0.03060 -0.1020 0.7510 1.0000
3.500 0.6969 0.04195 0.03138 -0.1020 0.7366 1.0000
3.750 0.7250 0.04269 0.03215 -0.1019 0.7221 1.0000
4.000 0.7538 0.04336 0.03284 -0.1018 0.7075 1.0000
4.250 0.7838 0.04390 0.03343 -0.1016 0.6928 1.0000
4.500 0.8128 0.04440 0.03397 -0.1012 0.6781 1.0000
4.750 0.8423 0.04475 0.03442 -0.1005 0.6634 1.0000
5.000 0.8723 0.04496 0.03470 -0.0998 0.6486 1.0000
5.250 0.9026 0.04503 0.03485 -0.0988 0.6339 1.0000
5.500 0.9335 0.04494 0.03489 -0.0977 0.6192 1.0000
6.000 0.9627 0.04729 0.03741 -0.0945 0.5841 1.0000
6.250 0.9920 0.04715 0.03738 -0.0931 0.5686 1.0000
6.500 1.0231 0.04676 0.03717 -0.0917 0.5533 1.0000
6.750 1.0571 0.04598 0.03652 -0.0902 0.5380 1.0000
7.000 1.0922 0.04503 0.03571 -0.0887 0.5224 1.0000
7.250 1.1319 0.04357 0.03441 -0.0872 0.5064 1.0000
7.500 1.1760 0.04166 0.03260 -0.0859 0.4899 1.0000
7.750 1.1993 0.04186 0.03292 -0.0842 0.4713 1.0000
8.000 1.2226 0.04207 0.03324 -0.0825 0.4520 1.0000
8.250 1.2617 0.04085 0.03208 -0.0813 0.4327 1.0000
8.500 1.2840 0.04132 0.03264 -0.0797 0.4130 1.0000
8.750 1.3046 0.04205 0.03348 -0.0781 0.3934 1.0000
9.000 1.3412 0.04150 0.03285 -0.0771 0.3728 1.0000
9.250 1.3516 0.04330 0.03486 -0.0752 0.3548 1.0000
9.500 1.3683 0.04460 0.03627 -0.0735 0.3364 1.0000
9.750 1.3921 0.04550 0.03719 -0.0722 0.3181 1.0000
10.000 1.4151 0.04665 0.03833 -0.0711 0.3004 1.0000
10.250 1.4268 0.04873 0.04058 -0.0693 0.2854 1.0000
10.500 1.4383 0.05080 0.04285 -0.0676 0.2709 1.0000
10.750 1.4509 0.05290 0.04508 -0.0659 0.2570 1.0000
11.000 1.4653 0.05504 0.04733 -0.0645 0.2437 1.0000
11.250 1.4382 0.05970 0.05248 -0.0610 0.2387 1.0000
11.500 1.0834 0.11138 0.10364 -0.0792 0.2848 1.0000
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Polar data table (+)
Polar graphs
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