S4310 (s4310-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4310 (s4310-il) Reynolds number: 200,000 Max Cl/Cd: 81.03 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4310-il-200000.txt Download as CSV file: xf-s4310-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2134 0.09843 0.09540 -0.0402 1.0000 0.0389
-9.500 -0.2244 0.09784 0.09490 -0.0367 1.0000 0.0395
-9.250 -0.2911 0.09945 0.09615 -0.0421 1.0000 0.0378
-9.000 -0.2814 0.09685 0.09358 -0.0408 1.0000 0.0389
-8.750 -0.2782 0.09442 0.09121 -0.0406 1.0000 0.0397
-8.500 -0.2821 0.09254 0.08941 -0.0395 1.0000 0.0405
-8.250 -0.3056 0.09262 0.08961 -0.0346 0.9997 0.0407
-8.000 -0.2853 0.08803 0.08503 -0.0410 0.9929 0.0427
-7.750 -0.2672 0.08191 0.07892 -0.0564 0.9810 0.0463
-7.500 -0.2380 0.07320 0.07008 -0.0782 0.9696 0.0470
-7.250 -0.2277 0.07013 0.06712 -0.0713 0.9661 0.0490
-7.000 -0.2028 0.06682 0.06378 -0.0750 0.9596 0.0512
-6.250 -0.1528 0.05164 0.04827 -0.0945 0.9248 0.0622
-6.000 -0.1379 0.04906 0.04561 -0.0950 0.9148 0.0650
-5.750 -0.1292 0.04433 0.04017 -0.0988 0.9013 0.0731
-5.500 -0.1131 0.04127 0.03726 -0.0980 0.8928 0.0749
-5.250 -0.0953 0.03919 0.03511 -0.0973 0.8853 0.0780
-5.000 -0.0789 0.03607 0.03150 -0.0979 0.8752 0.0881
-4.750 -0.0574 0.02603 0.02024 -0.0962 0.8691 0.0434
-4.500 -0.0349 0.02352 0.01728 -0.0953 0.8603 0.0430
-4.250 -0.0101 0.02167 0.01501 -0.0943 0.8547 0.0441
-4.000 0.0148 0.01991 0.01290 -0.0934 0.8461 0.0441
-3.750 0.0411 0.01859 0.01126 -0.0925 0.8405 0.0452
-3.500 0.0668 0.01753 0.01001 -0.0919 0.8324 0.0481
-3.250 0.0925 0.01645 0.00888 -0.0911 0.8265 0.0511
-3.000 0.1184 0.01576 0.00815 -0.0905 0.8189 0.0541
-2.750 0.1450 0.01530 0.00756 -0.0898 0.8125 0.0588
-2.500 0.1701 0.01450 0.00682 -0.0893 0.8054 0.0653
-2.250 0.1962 0.01393 0.00621 -0.0886 0.7987 0.0762
-2.000 0.2208 0.01289 0.00571 -0.0881 0.7921 0.1906
-1.750 0.2449 0.01218 0.00557 -0.0877 0.7849 0.3575
-1.500 0.2678 0.01154 0.00549 -0.0867 0.7788 0.5286
-1.250 0.2833 0.01077 0.00560 -0.0833 0.7713 0.7800
-1.000 0.3585 0.01031 0.00520 -0.0913 0.7668 0.9995
-0.750 0.3823 0.01039 0.00514 -0.0906 0.7583 1.0000
-0.500 0.4069 0.01043 0.00499 -0.0897 0.7522 1.0000
-0.250 0.4307 0.01053 0.00498 -0.0890 0.7437 1.0000
0.000 0.4561 0.01057 0.00485 -0.0883 0.7374 1.0000
0.250 0.4806 0.01068 0.00488 -0.0876 0.7287 1.0000
0.500 0.5068 0.01072 0.00476 -0.0871 0.7224 1.0000
0.750 0.5317 0.01082 0.00481 -0.0865 0.7132 1.0000
1.000 0.5581 0.01089 0.00474 -0.0860 0.7063 1.0000
1.250 0.5837 0.01097 0.00477 -0.0855 0.6973 1.0000
1.500 0.6100 0.01106 0.00476 -0.0850 0.6895 1.0000
1.750 0.6363 0.01113 0.00476 -0.0846 0.6811 1.0000
2.000 0.6623 0.01123 0.00481 -0.0841 0.6723 1.0000
2.250 0.6893 0.01130 0.00478 -0.0838 0.6646 1.0000
2.500 0.7150 0.01141 0.00488 -0.0833 0.6548 1.0000
2.750 0.7418 0.01150 0.00490 -0.0830 0.6465 1.0000
3.000 0.7681 0.01159 0.00495 -0.0826 0.6369 1.0000
3.250 0.7941 0.01170 0.00506 -0.0822 0.6269 1.0000
3.500 0.8206 0.01179 0.00509 -0.0818 0.6174 1.0000
3.750 0.8468 0.01189 0.00515 -0.0814 0.6068 1.0000
4.000 0.8725 0.01200 0.00526 -0.0809 0.5954 1.0000
4.250 0.8983 0.01212 0.00538 -0.0805 0.5840 1.0000
4.500 0.9242 0.01224 0.00547 -0.0800 0.5725 1.0000
4.750 0.9499 0.01237 0.00556 -0.0795 0.5605 1.0000
5.000 0.9752 0.01251 0.00568 -0.0790 0.5474 1.0000
5.250 1.0001 0.01267 0.00585 -0.0785 0.5333 1.0000
5.500 1.0248 0.01285 0.00602 -0.0779 0.5187 1.0000
5.750 1.0492 0.01305 0.00620 -0.0772 0.5034 1.0000
6.000 1.0730 0.01328 0.00645 -0.0766 0.4866 1.0000
6.250 1.0964 0.01353 0.00670 -0.0758 0.4689 1.0000
6.500 1.1193 0.01383 0.00697 -0.0750 0.4506 1.0000
6.750 1.1416 0.01417 0.00725 -0.0741 0.4321 1.0000
7.000 1.1633 0.01454 0.00762 -0.0732 0.4125 1.0000
7.250 1.1843 0.01496 0.00801 -0.0722 0.3926 1.0000
7.500 1.2044 0.01545 0.00842 -0.0710 0.3734 1.0000
7.750 1.2242 0.01593 0.00889 -0.0699 0.3536 1.0000
8.000 1.2430 0.01648 0.00940 -0.0686 0.3345 1.0000
8.250 1.2608 0.01708 0.00996 -0.0673 0.3165 1.0000
8.500 1.2781 0.01771 0.01056 -0.0658 0.2992 1.0000
8.750 1.2947 0.01834 0.01119 -0.0643 0.2825 1.0000
9.000 1.3102 0.01902 0.01186 -0.0627 0.2666 1.0000
9.250 1.3245 0.01973 0.01256 -0.0609 0.2514 1.0000
9.500 1.3370 0.02047 0.01332 -0.0588 0.2375 1.0000
9.750 1.3473 0.02125 0.01409 -0.0564 0.2246 1.0000
10.000 1.3565 0.02212 0.01494 -0.0541 0.2126 1.0000
10.250 1.3649 0.02308 0.01586 -0.0518 0.2009 1.0000
10.500 1.3743 0.02400 0.01685 -0.0497 0.1893 1.0000
10.750 1.3830 0.02504 0.01793 -0.0477 0.1782 1.0000
11.000 1.3905 0.02619 0.01911 -0.0458 0.1676 1.0000
11.250 1.3965 0.02748 0.02041 -0.0439 0.1576 1.0000
11.500 1.4021 0.02883 0.02178 -0.0422 0.1474 1.0000
11.750 1.4089 0.03016 0.02320 -0.0408 0.1371 1.0000
12.000 1.4144 0.03170 0.02478 -0.0394 0.1279 1.0000
12.250 1.4168 0.03350 0.02655 -0.0380 0.1195 1.0000
12.500 1.4243 0.03501 0.02820 -0.0370 0.1111 1.0000
12.750 1.4276 0.03694 0.03017 -0.0360 0.1042 1.0000
13.000 1.4317 0.03885 0.03215 -0.0351 0.0969 1.0000
13.250 1.4352 0.04090 0.03432 -0.0344 0.0902 1.0000
13.500 1.4366 0.04321 0.03667 -0.0338 0.0836 1.0000
13.750 1.4400 0.04542 0.03901 -0.0333 0.0775 1.0000
14.000 1.4391 0.04814 0.04178 -0.0330 0.0716 1.0000
14.250 1.4412 0.05066 0.04444 -0.0328 0.0645 1.0000
14.500 1.4386 0.05384 0.04767 -0.0329 0.0562 1.0000
14.750 1.4320 0.05765 0.05150 -0.0333 0.0476 1.0000
15.000 1.4212 0.06219 0.05606 -0.0339 0.0371 1.0000
15.250 1.4051 0.06767 0.06154 -0.0350 0.0300 1.0000
15.500 1.3934 0.07279 0.06677 -0.0362 0.0261 1.0000
15.750 1.3750 0.07912 0.07315 -0.0381 0.0237 1.0000
16.000 1.3657 0.08429 0.07849 -0.0397 0.0219 1.0000
16.250 1.3548 0.08988 0.08423 -0.0417 0.0205 1.0000
16.500 1.3447 0.09547 0.08994 -0.0438 0.0198 1.0000
16.750 1.3327 0.10152 0.09610 -0.0463 0.0190 1.0000
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