S4310 (s4310-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4310 (s4310-il) Reynolds number: 50,000 Max Cl/Cd: 36.32 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4310-il-50000-n5.txt Download as CSV file: xf-s4310-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4310
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2898 0.10800 0.10146 -0.0378 1.0000 0.1121
-8.750 -0.3032 0.10681 0.10044 -0.0398 1.0000 0.1139
-8.500 -0.3176 0.10554 0.09937 -0.0404 1.0000 0.1143
-8.250 -0.2957 0.10039 0.09422 -0.0375 1.0000 0.1177
-8.000 -0.3005 0.09837 0.09231 -0.0360 1.0000 0.1188
-7.500 -0.2586 0.08292 0.07743 -0.0385 0.9858 0.0653
-7.000 -0.3565 0.08502 0.07930 -0.0417 0.9888 0.0582
-6.750 -0.3375 0.08061 0.07484 -0.0449 0.9809 0.0564
-6.500 -0.3188 0.07539 0.06957 -0.0510 0.9715 0.0544
-6.250 -0.3018 0.06981 0.06388 -0.0575 0.9611 0.0524
-6.000 -0.2837 0.06354 0.05740 -0.0645 0.9511 0.0504
-5.750 -0.2605 0.05599 0.04937 -0.0725 0.9427 0.0482
-5.500 -0.2419 0.05139 0.04438 -0.0755 0.9327 0.0481
-5.250 -0.2153 0.04849 0.04129 -0.0781 0.9259 0.0503
-5.000 -0.1910 0.04518 0.03758 -0.0803 0.9176 0.0525
-4.750 -0.1625 0.04154 0.03339 -0.0826 0.9108 0.0537
-4.500 -0.1352 0.03842 0.02970 -0.0838 0.9031 0.0544
-4.250 -0.1034 0.03566 0.02629 -0.0852 0.8971 0.0563
-4.000 -0.0766 0.03370 0.02380 -0.0854 0.8891 0.0599
-3.750 -0.0418 0.03195 0.02182 -0.0869 0.8842 0.0640
-3.500 -0.0182 0.03069 0.02027 -0.0860 0.8753 0.0669
-3.250 0.0169 0.02931 0.01854 -0.0869 0.8702 0.0731
-3.000 0.0401 0.02854 0.01770 -0.0862 0.8614 0.0806
-2.750 0.0742 0.02747 0.01644 -0.0868 0.8560 0.0896
-2.500 0.0985 0.02684 0.01574 -0.0862 0.8476 0.1046
-2.250 0.1306 0.02588 0.01489 -0.0869 0.8417 0.1448
-2.000 0.1537 0.02494 0.01453 -0.0866 0.8334 0.2523
-1.750 0.1771 0.02364 0.01435 -0.0858 0.8272 0.4898
-1.500 0.2395 0.02220 0.01389 -0.0894 0.8247 1.0000
-1.250 0.2592 0.02250 0.01380 -0.0882 0.8147 1.0000
-1.000 0.2858 0.02269 0.01362 -0.0880 0.8072 1.0000
-0.750 0.3106 0.02292 0.01354 -0.0876 0.7989 1.0000
-0.500 0.3345 0.02319 0.01354 -0.0870 0.7905 1.0000
-0.250 0.3621 0.02336 0.01345 -0.0868 0.7832 1.0000
0.000 0.3842 0.02370 0.01358 -0.0859 0.7740 1.0000
0.250 0.4139 0.02381 0.01348 -0.0860 0.7675 1.0000
0.500 0.4345 0.02421 0.01372 -0.0849 0.7577 1.0000
0.750 0.4660 0.02425 0.01358 -0.0851 0.7518 1.0000
1.000 0.4854 0.02471 0.01392 -0.0840 0.7413 1.0000
1.250 0.5115 0.02493 0.01401 -0.0835 0.7334 1.0000
1.500 0.5371 0.02517 0.01414 -0.0830 0.7249 1.0000
1.750 0.5595 0.02554 0.01443 -0.0821 0.7153 1.0000
2.000 0.5896 0.02556 0.01436 -0.0820 0.7085 1.0000
2.250 0.6100 0.02601 0.01476 -0.0809 0.6977 1.0000
2.500 0.6359 0.02621 0.01491 -0.0804 0.6891 1.0000
2.750 0.6626 0.02635 0.01501 -0.0798 0.6803 1.0000
3.000 0.6841 0.02674 0.01538 -0.0788 0.6695 1.0000
3.250 0.7118 0.02681 0.01542 -0.0783 0.6611 1.0000
3.500 0.7369 0.02700 0.01560 -0.0776 0.6512 1.0000
3.750 0.7584 0.02737 0.01601 -0.0766 0.6399 1.0000
4.000 0.7838 0.02753 0.01617 -0.0758 0.6299 1.0000
4.250 0.8124 0.02749 0.01613 -0.0753 0.6208 1.0000
4.500 0.8333 0.02787 0.01656 -0.0742 0.6086 1.0000
4.750 0.8557 0.02816 0.01692 -0.0732 0.5968 1.0000
5.000 0.8804 0.02831 0.01712 -0.0723 0.5856 1.0000
5.250 0.9090 0.02820 0.01703 -0.0717 0.5753 1.0000
5.500 0.9318 0.02843 0.01732 -0.0707 0.5626 1.0000
5.750 0.9534 0.02871 0.01771 -0.0695 0.5492 1.0000
6.000 0.9754 0.02896 0.01803 -0.0684 0.5356 1.0000
6.250 0.9974 0.02920 0.01834 -0.0672 0.5216 1.0000
6.500 1.0195 0.02944 0.01865 -0.0660 0.5074 1.0000
6.750 1.0413 0.02968 0.01899 -0.0648 0.4927 1.0000
7.000 1.0629 0.02995 0.01933 -0.0636 0.4776 1.0000
7.250 1.0841 0.03024 0.01968 -0.0623 0.4622 1.0000
7.500 1.1051 0.03056 0.02005 -0.0611 0.4465 1.0000
7.750 1.1248 0.03097 0.02053 -0.0597 0.4304 1.0000
8.000 1.1410 0.03161 0.02126 -0.0581 0.4136 1.0000
8.250 1.1570 0.03227 0.02199 -0.0565 0.3969 1.0000
8.500 1.1727 0.03297 0.02274 -0.0548 0.3804 1.0000
8.750 1.1878 0.03371 0.02354 -0.0532 0.3642 1.0000
9.000 1.2019 0.03452 0.02443 -0.0514 0.3484 1.0000
9.250 1.2141 0.03542 0.02536 -0.0495 0.3332 1.0000
9.500 1.2252 0.03641 0.02641 -0.0476 0.3184 1.0000
9.750 1.2352 0.03752 0.02757 -0.0457 0.3040 1.0000
10.000 1.2446 0.03875 0.02886 -0.0440 0.2903 1.0000
10.250 1.2529 0.04008 0.03026 -0.0422 0.2769 1.0000
10.500 1.2607 0.04151 0.03181 -0.0406 0.2642 1.0000
10.750 1.2686 0.04300 0.03339 -0.0390 0.2521 1.0000
11.000 1.2763 0.04453 0.03497 -0.0376 0.2404 1.0000
11.250 1.2855 0.04599 0.03647 -0.0363 0.2293 1.0000
11.500 1.2874 0.04813 0.03880 -0.0349 0.2187 1.0000
11.750 1.2912 0.05018 0.04098 -0.0337 0.2088 1.0000
12.000 1.2980 0.05198 0.04283 -0.0327 0.1992 1.0000
12.250 1.2998 0.05434 0.04541 -0.0317 0.1902 1.0000
12.500 1.3013 0.05683 0.04806 -0.0309 0.1819 1.0000
12.750 1.3097 0.05855 0.04975 -0.0300 0.1734 1.0000
13.000 1.3020 0.06220 0.05373 -0.0297 0.1663 1.0000
13.250 1.3098 0.06412 0.05567 -0.0290 0.1589 1.0000
13.500 1.2990 0.06836 0.06021 -0.0291 0.1527 1.0000
13.750 1.3066 0.07027 0.06211 -0.0286 0.1456 1.0000
14.000 1.2899 0.07558 0.06776 -0.0295 0.1408 1.0000
14.250 1.2892 0.07877 0.07106 -0.0296 0.1350 1.0000
14.500 1.2805 0.08327 0.07574 -0.0305 0.1303 1.0000
14.750 1.2579 0.09017 0.08292 -0.0328 0.1267 1.0000
15.000 1.2741 0.09065 0.08331 -0.0319 0.1196 1.0000
15.250 1.2414 0.09985 0.09284 -0.0359 0.1178 1.0000
15.500 1.1982 0.11207 0.10530 -0.0421 0.1168 1.0000
15.750 1.1158 0.13553 0.12875 -0.0556 0.1168 1.0000
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Polar data table (+)
Polar graphs
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