S4310 (s4310-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4310 (s4310-il) Reynolds number: 200,000 Max Cl/Cd: 78.5 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4310-il-200000-n5.txt Download as CSV file: xf-s4310-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2990 0.10291 0.09947 -0.0411 1.0000 0.0215
-9.250 -0.2959 0.09377 0.09039 -0.0422 1.0000 0.0159
-9.000 -0.2933 0.09107 0.08775 -0.0424 1.0000 0.0157
-8.750 -0.2816 0.08729 0.08399 -0.0457 0.9841 0.0154
-8.500 -0.2673 0.08276 0.07945 -0.0508 0.9674 0.0151
-8.250 -0.2544 0.07755 0.07424 -0.0567 0.9513 0.0150
-8.000 -0.2438 0.07268 0.06935 -0.0622 0.9342 0.0148
-7.500 -0.2444 0.06118 0.05779 -0.0739 0.8961 0.0155
-7.250 -0.2473 0.05191 0.04835 -0.0819 0.8800 0.0159
-7.000 -0.2433 0.04622 0.04244 -0.0849 0.8686 0.0157
-6.750 -0.2412 0.03894 0.03471 -0.0875 0.8573 0.0158
-6.500 -0.2328 0.03347 0.02870 -0.0884 0.8477 0.0158
-6.250 -0.2191 0.02912 0.02369 -0.0883 0.8400 0.0159
-6.000 -0.2011 0.02586 0.01989 -0.0880 0.8315 0.0163
-5.750 -0.1799 0.02386 0.01757 -0.0876 0.8249 0.0168
-5.500 -0.1564 0.02234 0.01577 -0.0873 0.8169 0.0174
-5.250 -0.1323 0.02097 0.01410 -0.0868 0.8106 0.0182
-5.000 -0.1068 0.01995 0.01280 -0.0865 0.8029 0.0199
-4.750 -0.0808 0.01903 0.01152 -0.0859 0.7965 0.0214
-4.500 -0.0557 0.01755 0.00989 -0.0856 0.7893 0.0224
-4.250 -0.0299 0.01670 0.00891 -0.0852 0.7828 0.0236
-4.000 -0.0036 0.01602 0.00813 -0.0848 0.7758 0.0253
-3.750 0.0230 0.01550 0.00747 -0.0845 0.7692 0.0277
-3.500 0.0491 0.01477 0.00665 -0.0841 0.7627 0.0293
-3.250 0.0755 0.01421 0.00603 -0.0838 0.7559 0.0312
-3.000 0.1023 0.01384 0.00558 -0.0835 0.7497 0.0343
-2.750 0.1293 0.01348 0.00514 -0.0833 0.7426 0.0374
-2.250 0.1835 0.01280 0.00435 -0.0828 0.7295 0.0494
-2.000 0.2104 0.01242 0.00405 -0.0826 0.7234 0.0789
-1.750 0.2371 0.01205 0.00387 -0.0825 0.7164 0.1377
-1.500 0.2638 0.01174 0.00371 -0.0823 0.7098 0.2020
-1.250 0.2898 0.01131 0.00364 -0.0822 0.7031 0.3105
-1.000 0.3142 0.01073 0.00361 -0.0818 0.6963 0.4720
-0.750 0.3362 0.01016 0.00362 -0.0804 0.6898 0.6485
-0.500 0.3563 0.00973 0.00367 -0.0779 0.6828 0.8213
-0.250 0.3972 0.00959 0.00355 -0.0798 0.6762 0.9488
0.000 0.4438 0.00956 0.00340 -0.0837 0.6682 1.0000
0.250 0.4694 0.00964 0.00334 -0.0832 0.6611 1.0000
0.500 0.4951 0.00971 0.00332 -0.0827 0.6531 1.0000
0.750 0.5211 0.00980 0.00330 -0.0823 0.6454 1.0000
1.000 0.5471 0.00989 0.00329 -0.0819 0.6370 1.0000
1.250 0.5733 0.00999 0.00330 -0.0815 0.6285 1.0000
1.500 0.5995 0.01009 0.00330 -0.0812 0.6204 1.0000
1.750 0.6258 0.01019 0.00335 -0.0808 0.6111 1.0000
2.000 0.6521 0.01030 0.00339 -0.0805 0.6026 1.0000
2.250 0.6784 0.01042 0.00344 -0.0802 0.5933 1.0000
2.500 0.7047 0.01054 0.00352 -0.0799 0.5838 1.0000
2.750 0.7309 0.01067 0.00359 -0.0795 0.5747 1.0000
3.000 0.7571 0.01080 0.00368 -0.0792 0.5642 1.0000
3.250 0.7832 0.01094 0.00380 -0.0789 0.5535 1.0000
3.500 0.8091 0.01110 0.00391 -0.0785 0.5424 1.0000
3.750 0.8348 0.01126 0.00403 -0.0781 0.5307 1.0000
4.000 0.8604 0.01144 0.00416 -0.0777 0.5182 1.0000
4.250 0.8858 0.01163 0.00433 -0.0773 0.5050 1.0000
4.500 0.9110 0.01183 0.00450 -0.0769 0.4911 1.0000
4.750 0.9360 0.01205 0.00468 -0.0764 0.4768 1.0000
5.000 0.9606 0.01229 0.00488 -0.0759 0.4617 1.0000
5.250 0.9848 0.01256 0.00513 -0.0753 0.4461 1.0000
5.500 1.0087 0.01285 0.00537 -0.0748 0.4297 1.0000
5.750 1.0323 0.01315 0.00565 -0.0741 0.4126 1.0000
6.000 1.0554 0.01349 0.00594 -0.0734 0.3949 1.0000
6.250 1.0779 0.01386 0.00629 -0.0727 0.3771 1.0000
6.500 1.0997 0.01428 0.00665 -0.0718 0.3592 1.0000
6.750 1.1213 0.01470 0.00703 -0.0710 0.3416 1.0000
7.000 1.1424 0.01515 0.00744 -0.0701 0.3239 1.0000
7.250 1.1629 0.01562 0.00790 -0.0691 0.3071 1.0000
7.500 1.1827 0.01613 0.00838 -0.0680 0.2904 1.0000
7.750 1.2019 0.01666 0.00888 -0.0669 0.2749 1.0000
8.000 1.2205 0.01721 0.00941 -0.0657 0.2600 1.0000
8.250 1.2384 0.01778 0.00999 -0.0644 0.2458 1.0000
8.500 1.2557 0.01837 0.01057 -0.0630 0.2321 1.0000
8.750 1.2722 0.01897 0.01119 -0.0615 0.2194 1.0000
9.000 1.2872 0.01959 0.01182 -0.0599 0.2077 1.0000
9.250 1.2998 0.02025 0.01250 -0.0578 0.1964 1.0000
9.500 1.3114 0.02100 0.01326 -0.0557 0.1856 1.0000
9.750 1.3233 0.02177 0.01406 -0.0538 0.1753 1.0000
10.000 1.3352 0.02257 0.01491 -0.0520 0.1656 1.0000
10.250 1.3456 0.02350 0.01586 -0.0502 0.1562 1.0000
10.500 1.3550 0.02452 0.01690 -0.0484 0.1471 1.0000
10.750 1.3659 0.02551 0.01795 -0.0468 0.1384 1.0000
11.000 1.3744 0.02668 0.01915 -0.0452 0.1301 1.0000
11.250 1.3819 0.02798 0.02048 -0.0437 0.1206 1.0000
11.500 1.3902 0.02927 0.02183 -0.0423 0.1109 1.0000
11.750 1.3970 0.03074 0.02331 -0.0410 0.1015 1.0000
12.000 1.4021 0.03239 0.02497 -0.0397 0.0930 1.0000
12.250 1.4075 0.03408 0.02668 -0.0386 0.0837 1.0000
12.500 1.4136 0.03577 0.02844 -0.0376 0.0767 1.0000
12.750 1.4166 0.03780 0.03049 -0.0366 0.0701 1.0000
13.000 1.4222 0.03965 0.03243 -0.0359 0.0637 1.0000
13.250 1.4243 0.04190 0.03472 -0.0352 0.0580 1.0000
13.500 1.4269 0.04416 0.03706 -0.0346 0.0513 1.0000
13.750 1.4282 0.04663 0.03960 -0.0342 0.0461 1.0000
14.000 1.4288 0.04925 0.04230 -0.0338 0.0408 1.0000
14.250 1.4282 0.05211 0.04523 -0.0337 0.0356 1.0000
14.500 1.4246 0.05543 0.04859 -0.0337 0.0297 1.0000
14.750 1.4208 0.05891 0.05214 -0.0340 0.0247 1.0000
15.000 1.4151 0.06276 0.05606 -0.0345 0.0203 1.0000
15.250 1.4070 0.06710 0.06048 -0.0353 0.0164 1.0000
15.500 1.3998 0.07149 0.06497 -0.0363 0.0142 1.0000
15.750 1.3905 0.07637 0.06996 -0.0377 0.0120 1.0000
16.000 1.3820 0.08128 0.07500 -0.0392 0.0109 1.0000
16.250 1.3712 0.08676 0.08061 -0.0411 0.0100 1.0000
16.500 1.3624 0.09208 0.08608 -0.0431 0.0097 1.0000
16.750 1.3524 0.09777 0.09194 -0.0454 0.0092 1.0000
17.000 1.3409 0.10389 0.09822 -0.0481 0.0087 1.0000
17.250 1.3297 0.11010 0.10459 -0.0509 0.0085 1.0000
17.500 1.3174 0.11667 0.11132 -0.0541 0.0083 1.0000
17.750 1.3052 0.12337 0.11819 -0.0575 0.0082 1.0000
18.000 1.2929 0.13026 0.12523 -0.0611 0.0081 1.0000
18.250 1.2802 0.13737 0.13248 -0.0649 0.0079 1.0000
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Polar data table (+)
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