S4310 (s4310-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4310 (s4310-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.7 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4310-il-1000000.txt Download as CSV file: xf-s4310-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3011 0.10671 0.10512 -0.0340 1.0000 0.0103
-10.000 -0.2971 0.10337 0.10179 -0.0352 1.0000 0.0104
-9.750 -0.2929 0.10013 0.09857 -0.0365 1.0000 0.0108
-9.500 -0.2827 0.09432 0.09277 -0.0423 0.9777 0.0117
-9.250 -0.2606 0.08850 0.08693 -0.0502 0.9643 0.0118
-9.000 -0.2403 0.08285 0.08122 -0.0576 0.9464 0.0119
-8.750 -0.2319 0.07854 0.07682 -0.0612 0.9194 0.0119
-8.500 -0.2314 0.07502 0.07321 -0.0625 0.8963 0.0119
-8.250 -0.2336 0.07130 0.06944 -0.0637 0.8776 0.0119
-8.000 -0.2366 0.06781 0.06589 -0.0649 0.8609 0.0119
-7.750 -0.2481 0.06367 0.06173 -0.0663 0.8448 0.0119
-7.500 -0.3127 0.04039 0.03814 -0.0822 0.8258 0.0090
-7.250 -0.3009 0.03673 0.03430 -0.0836 0.8166 0.0093
-7.000 -0.3320 0.01690 0.01250 -0.0836 0.8072 0.0091
-6.750 -0.3066 0.01625 0.01174 -0.0834 0.7996 0.0094
-6.500 -0.2807 0.01565 0.01102 -0.0833 0.7927 0.0097
-6.250 -0.2547 0.01496 0.01019 -0.0831 0.7853 0.0101
-6.000 -0.2288 0.01413 0.00918 -0.0828 0.7787 0.0104
-5.750 -0.2025 0.01334 0.00824 -0.0826 0.7715 0.0109
-5.500 -0.1758 0.01272 0.00746 -0.0824 0.7649 0.0114
-5.250 -0.1480 0.01246 0.00710 -0.0823 0.7579 0.0118
-5.000 -0.1226 0.01141 0.00592 -0.0820 0.7514 0.0130
-4.750 -0.0947 0.01117 0.00566 -0.0820 0.7447 0.0138
-4.500 -0.0672 0.01084 0.00524 -0.0818 0.7381 0.0147
-4.250 -0.0393 0.01054 0.00487 -0.0818 0.7316 0.0156
-4.000 -0.0124 0.00994 0.00417 -0.0816 0.7250 0.0166
-3.750 0.0148 0.00947 0.00366 -0.0815 0.7188 0.0181
-3.500 0.0428 0.00923 0.00338 -0.0814 0.7121 0.0194
-3.250 0.0708 0.00908 0.00317 -0.0814 0.7059 0.0208
-3.000 0.0988 0.00881 0.00285 -0.0813 0.6992 0.0219
-2.500 0.1546 0.00823 0.00216 -0.0812 0.6865 0.0257
-2.250 0.1827 0.00809 0.00196 -0.0811 0.6800 0.0273
-2.000 0.2111 0.00796 0.00179 -0.0811 0.6737 0.0285
-1.750 0.2393 0.00778 0.00159 -0.0811 0.6670 0.0340
-1.500 0.2672 0.00754 0.00145 -0.0811 0.6607 0.0675
-1.250 0.2949 0.00723 0.00136 -0.0812 0.6537 0.1409
-1.000 0.3226 0.00702 0.00131 -0.0812 0.6470 0.2051
-0.750 0.3503 0.00677 0.00128 -0.0813 0.6396 0.2843
-0.500 0.3777 0.00652 0.00126 -0.0813 0.6327 0.3797
-0.250 0.4051 0.00624 0.00125 -0.0814 0.6253 0.4856
0.000 0.4315 0.00590 0.00128 -0.0812 0.6183 0.6264
0.250 0.4560 0.00548 0.00133 -0.0805 0.6110 0.7875
0.500 0.4776 0.00527 0.00139 -0.0787 0.6042 0.9010
0.750 0.5117 0.00519 0.00139 -0.0797 0.5963 0.9816
1.000 0.5560 0.00524 0.00136 -0.0832 0.5880 0.9994
1.250 0.5832 0.00531 0.00138 -0.0831 0.5798 1.0000
1.500 0.6097 0.00538 0.00140 -0.0828 0.5715 1.0000
1.750 0.6362 0.00548 0.00143 -0.0825 0.5624 1.0000
2.000 0.6633 0.00555 0.00146 -0.0823 0.5530 1.0000
2.250 0.6903 0.00565 0.00151 -0.0821 0.5433 1.0000
2.500 0.7172 0.00576 0.00156 -0.0819 0.5329 1.0000
2.750 0.7445 0.00586 0.00162 -0.0818 0.5224 1.0000
3.000 0.7716 0.00597 0.00168 -0.0817 0.5111 1.0000
3.250 0.7986 0.00610 0.00176 -0.0816 0.4992 1.0000
3.500 0.8255 0.00624 0.00185 -0.0814 0.4870 1.0000
3.750 0.8523 0.00640 0.00194 -0.0813 0.4736 1.0000
4.000 0.8790 0.00656 0.00205 -0.0811 0.4596 1.0000
4.250 0.9056 0.00673 0.00217 -0.0810 0.4448 1.0000
4.500 0.9321 0.00692 0.00230 -0.0808 0.4292 1.0000
4.750 0.9584 0.00712 0.00244 -0.0806 0.4128 1.0000
5.000 0.9844 0.00735 0.00260 -0.0804 0.3951 1.0000
5.250 1.0101 0.00760 0.00278 -0.0802 0.3769 1.0000
5.500 1.0354 0.00788 0.00297 -0.0798 0.3584 1.0000
5.750 1.0609 0.00814 0.00317 -0.0796 0.3405 1.0000
6.000 1.0860 0.00843 0.00339 -0.0792 0.3217 1.0000
6.250 1.1107 0.00874 0.00362 -0.0789 0.3039 1.0000
6.750 1.1597 0.00937 0.00412 -0.0781 0.2714 1.0000
7.000 1.1840 0.00969 0.00439 -0.0776 0.2566 1.0000
7.250 1.2080 0.01002 0.00466 -0.0772 0.2412 1.0000
7.500 1.2314 0.01038 0.00496 -0.0766 0.2250 1.0000
7.750 1.2544 0.01076 0.00527 -0.0760 0.2085 1.0000
8.000 1.2769 0.01116 0.00561 -0.0754 0.1927 1.0000
8.250 1.2992 0.01156 0.00595 -0.0747 0.1790 1.0000
8.500 1.3204 0.01201 0.00633 -0.0738 0.1636 1.0000
8.750 1.3409 0.01250 0.00674 -0.0729 0.1484 1.0000
9.000 1.3613 0.01296 0.00716 -0.0719 0.1357 1.0000
9.250 1.3807 0.01345 0.00759 -0.0708 0.1228 1.0000
9.500 1.3996 0.01395 0.00805 -0.0696 0.1112 1.0000
9.750 1.4175 0.01447 0.00852 -0.0683 0.1004 1.0000
10.000 1.4338 0.01502 0.00904 -0.0667 0.0898 1.0000
10.250 1.4468 0.01558 0.00956 -0.0645 0.0811 1.0000
10.500 1.4578 0.01621 0.01016 -0.0621 0.0721 1.0000
10.750 1.4693 0.01684 0.01078 -0.0599 0.0642 1.0000
11.000 1.4789 0.01762 0.01152 -0.0575 0.0552 1.0000
11.250 1.4873 0.01852 0.01237 -0.0552 0.0462 1.0000
11.500 1.4930 0.01962 0.01342 -0.0527 0.0357 1.0000
11.750 1.4916 0.02125 0.01493 -0.0497 0.0214 1.0000
12.000 1.4898 0.02304 0.01667 -0.0469 0.0106 1.0000
12.250 1.4917 0.02468 0.01832 -0.0447 0.0064 1.0000
12.500 1.4984 0.02607 0.01977 -0.0432 0.0055 1.0000
12.750 1.5053 0.02750 0.02128 -0.0417 0.0049 1.0000
13.000 1.5128 0.02892 0.02277 -0.0405 0.0046 1.0000
13.250 1.5188 0.03053 0.02446 -0.0393 0.0044 1.0000
13.500 1.5231 0.03235 0.02636 -0.0382 0.0041 1.0000
13.750 1.5251 0.03446 0.02855 -0.0371 0.0038 1.0000
14.000 1.5272 0.03662 0.03081 -0.0362 0.0036 1.0000
14.250 1.5252 0.03928 0.03359 -0.0353 0.0035 1.0000
14.500 1.5256 0.04179 0.03620 -0.0347 0.0034 1.0000
14.750 1.5264 0.04435 0.03886 -0.0343 0.0034 1.0000
15.000 1.5274 0.04701 0.04161 -0.0341 0.0034 1.0000
15.250 1.5261 0.05003 0.04474 -0.0341 0.0033 1.0000
15.500 1.5252 0.05311 0.04792 -0.0342 0.0033 1.0000
15.750 1.5205 0.05680 0.05173 -0.0346 0.0032 1.0000
16.000 1.5157 0.06065 0.05569 -0.0352 0.0032 1.0000
16.250 1.5103 0.06471 0.05987 -0.0361 0.0031 1.0000
16.500 1.5059 0.06877 0.06404 -0.0371 0.0031 1.0000
16.750 1.4973 0.07362 0.06900 -0.0385 0.0031 1.0000
17.000 1.4880 0.07873 0.07424 -0.0402 0.0030 1.0000
17.250 1.4782 0.08407 0.07970 -0.0421 0.0030 1.0000
17.500 1.4675 0.08975 0.08550 -0.0443 0.0030 1.0000
17.750 1.4559 0.09573 0.09161 -0.0468 0.0029 1.0000
18.000 1.4448 0.10175 0.09775 -0.0494 0.0029 1.0000
18.250 1.4293 0.10876 0.10489 -0.0526 0.0029 1.0000
18.500 1.4170 0.11529 0.11155 -0.0557 0.0029 1.0000
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