S4320 (s4320-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4320 (s4320-il) Reynolds number: 500,000 Max Cl/Cd: 106.44 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4320-il-500000-n5.txt Download as CSV file: xf-s4320-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3071 0.10516 0.10289 -0.0276 1.0000 0.0065
-9.500 -0.3058 0.10068 0.09844 -0.0294 1.0000 0.0067
-9.250 -0.3031 0.09687 0.09465 -0.0309 1.0000 0.0067
-8.750 -0.2771 0.08729 0.08507 -0.0405 0.9561 0.0068
-8.500 -0.2565 0.08216 0.07989 -0.0476 0.9301 0.0070
-8.250 -0.2376 0.08048 0.07811 -0.0501 0.9021 0.0074
-8.000 -0.2301 0.07809 0.07564 -0.0514 0.8773 0.0078
-7.750 -0.2308 0.07448 0.07196 -0.0526 0.8557 0.0076
-7.500 -0.2280 0.07202 0.06944 -0.0533 0.8380 0.0082
-7.250 -0.2286 0.06900 0.06638 -0.0546 0.8221 0.0085
-7.000 -0.2250 0.06500 0.06233 -0.0581 0.8085 0.0085
-6.750 -0.2186 0.06027 0.05755 -0.0630 0.7961 0.0084
-6.500 -0.2087 0.05413 0.05133 -0.0699 0.7850 0.0084
-6.250 -0.1944 0.04604 0.04309 -0.0785 0.7754 0.0085
-6.000 -0.1853 0.02001 0.01521 -0.0927 0.7687 0.0097
-5.750 -0.1600 0.01829 0.01321 -0.0932 0.7608 0.0101
-5.500 -0.1332 0.01784 0.01264 -0.0933 0.7527 0.0105
-5.250 -0.1061 0.01722 0.01188 -0.0934 0.7451 0.0112
-5.000 -0.0790 0.01623 0.01062 -0.0935 0.7375 0.0120
-4.750 -0.0514 0.01507 0.00916 -0.0935 0.7304 0.0126
-4.500 -0.0237 0.01428 0.00812 -0.0935 0.7231 0.0131
-4.250 0.0042 0.01367 0.00731 -0.0934 0.7162 0.0134
-4.000 0.0314 0.01256 0.00605 -0.0935 0.7091 0.0142
-3.750 0.0592 0.01214 0.00558 -0.0935 0.7024 0.0151
-3.500 0.0871 0.01172 0.00506 -0.0935 0.6954 0.0159
-3.250 0.1151 0.01126 0.00450 -0.0934 0.6889 0.0165
-3.000 0.1432 0.01086 0.00401 -0.0934 0.6820 0.0171
-2.750 0.1713 0.01053 0.00360 -0.0933 0.6756 0.0176
-2.500 0.1996 0.01025 0.00325 -0.0933 0.6685 0.0181
-2.250 0.2277 0.00992 0.00284 -0.0933 0.6621 0.0191
-2.000 0.2561 0.00965 0.00253 -0.0934 0.6550 0.0204
-1.500 0.3128 0.00933 0.00209 -0.0933 0.6410 0.0226
-1.000 0.3695 0.00912 0.00178 -0.0933 0.6263 0.0276
-0.750 0.3976 0.00895 0.00167 -0.0933 0.6188 0.0562
-0.500 0.4259 0.00870 0.00161 -0.0934 0.6106 0.1195
-0.250 0.4539 0.00850 0.00158 -0.0936 0.6027 0.1931
0.000 0.4820 0.00835 0.00156 -0.0937 0.5940 0.2577
0.250 0.5099 0.00816 0.00157 -0.0938 0.5857 0.3416
0.500 0.5371 0.00774 0.00164 -0.0939 0.5769 0.5292
0.750 0.5610 0.00715 0.00176 -0.0931 0.5684 0.7704
1.000 0.5880 0.00678 0.00172 -0.0923 0.5596 1.0000
1.250 0.6162 0.00687 0.00173 -0.0923 0.5500 1.0000
1.500 0.6442 0.00698 0.00176 -0.0923 0.5400 1.0000
1.750 0.6721 0.00709 0.00180 -0.0923 0.5295 1.0000
2.000 0.6998 0.00722 0.00184 -0.0922 0.5179 1.0000
2.250 0.7276 0.00734 0.00190 -0.0921 0.5054 1.0000
2.500 0.7552 0.00748 0.00197 -0.0921 0.4925 1.0000
2.750 0.7826 0.00764 0.00205 -0.0920 0.4793 1.0000
3.000 0.8100 0.00780 0.00215 -0.0919 0.4649 1.0000
3.250 0.8371 0.00798 0.00225 -0.0918 0.4502 1.0000
3.500 0.8641 0.00818 0.00239 -0.0917 0.4348 1.0000
3.750 0.8910 0.00840 0.00253 -0.0915 0.4188 1.0000
4.250 0.9441 0.00887 0.00285 -0.0912 0.3850 1.0000
4.500 0.9705 0.00913 0.00305 -0.0910 0.3673 1.0000
4.750 0.9966 0.00941 0.00325 -0.0908 0.3493 1.0000
5.000 1.0224 0.00971 0.00347 -0.0906 0.3320 1.0000
5.250 1.0481 0.01002 0.00371 -0.0903 0.3145 1.0000
5.500 1.0737 0.01034 0.00398 -0.0901 0.2975 1.0000
5.750 1.0991 0.01067 0.00425 -0.0898 0.2811 1.0000
6.000 1.1243 0.01100 0.00453 -0.0895 0.2655 1.0000
6.250 1.1493 0.01136 0.00483 -0.0892 0.2501 1.0000
6.500 1.1740 0.01172 0.00516 -0.0888 0.2352 1.0000
6.750 1.1985 0.01210 0.00549 -0.0884 0.2207 1.0000
7.000 1.2230 0.01246 0.00582 -0.0881 0.2086 1.0000
7.250 1.2471 0.01285 0.00618 -0.0876 0.1960 1.0000
7.500 1.2707 0.01327 0.00658 -0.0871 0.1828 1.0000
7.750 1.2942 0.01369 0.00698 -0.0866 0.1719 1.0000
8.000 1.3169 0.01417 0.00741 -0.0860 0.1589 1.0000
8.250 1.3388 0.01469 0.00788 -0.0854 0.1440 1.0000
8.500 1.3605 0.01521 0.00838 -0.0846 0.1314 1.0000
8.750 1.3813 0.01578 0.00891 -0.0838 0.1181 1.0000
9.000 1.4011 0.01641 0.00948 -0.0829 0.1035 1.0000
9.250 1.4202 0.01706 0.01008 -0.0818 0.0904 1.0000
9.500 1.4388 0.01771 0.01071 -0.0807 0.0803 1.0000
9.750 1.4561 0.01841 0.01139 -0.0795 0.0703 1.0000
10.000 1.4718 0.01919 0.01212 -0.0780 0.0596 1.0000
10.250 1.4864 0.01995 0.01288 -0.0764 0.0509 1.0000
10.500 1.4978 0.02073 0.01366 -0.0742 0.0431 1.0000
10.750 1.5047 0.02174 0.01463 -0.0715 0.0336 1.0000
11.000 1.5094 0.02295 0.01580 -0.0689 0.0244 1.0000
11.250 1.5114 0.02444 0.01726 -0.0662 0.0146 1.0000
11.500 1.5120 0.02615 0.01896 -0.0638 0.0080 1.0000
11.750 1.5169 0.02766 0.02055 -0.0619 0.0063 1.0000
12.000 1.5217 0.02928 0.02225 -0.0603 0.0053 1.0000
12.250 1.5277 0.03088 0.02394 -0.0589 0.0049 1.0000
12.500 1.5337 0.03257 0.02574 -0.0578 0.0045 1.0000
12.750 1.5385 0.03443 0.02771 -0.0567 0.0043 1.0000
13.000 1.5427 0.03644 0.02984 -0.0558 0.0041 1.0000
13.250 1.5454 0.03867 0.03218 -0.0550 0.0039 1.0000
13.500 1.5463 0.04118 0.03480 -0.0544 0.0037 1.0000
13.750 1.5457 0.04396 0.03771 -0.0540 0.0035 1.0000
14.000 1.5437 0.04699 0.04088 -0.0537 0.0034 1.0000
14.250 1.5405 0.05031 0.04433 -0.0537 0.0032 1.0000
14.500 1.5387 0.05354 0.04768 -0.0538 0.0031 1.0000
14.750 1.5357 0.05707 0.05135 -0.0542 0.0031 1.0000
15.000 1.5321 0.06085 0.05526 -0.0549 0.0030 1.0000
15.250 1.5262 0.06508 0.05963 -0.0558 0.0029 1.0000
15.500 1.5214 0.06933 0.06400 -0.0569 0.0028 1.0000
15.750 1.5149 0.07401 0.06882 -0.0583 0.0027 1.0000
16.000 1.5050 0.07942 0.07437 -0.0601 0.0027 1.0000
16.250 1.4969 0.08468 0.07977 -0.0621 0.0026 1.0000
16.500 1.4860 0.09065 0.08588 -0.0645 0.0026 1.0000
16.750 1.4740 0.09695 0.09233 -0.0672 0.0025 1.0000
17.000 1.4624 0.10339 0.09891 -0.0700 0.0025 1.0000
17.250 1.4495 0.11022 0.10589 -0.0732 0.0025 1.0000
17.500 1.4364 0.11723 0.11304 -0.0767 0.0025 1.0000
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Polar data table (+)
Polar graphs
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