S4310 (s4310-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4310 (s4310-il) Reynolds number: 100,000 Max Cl/Cd: 58.27 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4310-il-100000-n5.txt Download as CSV file: xf-s4310-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2788 0.09790 0.09331 -0.0400 1.0000 0.0539
-8.500 -0.2818 0.09548 0.09098 -0.0400 1.0000 0.0545
-8.250 -0.2908 0.09359 0.08922 -0.0389 1.0000 0.0548
-8.000 -0.2825 0.08974 0.08540 -0.0424 0.9890 0.0543
-7.750 -0.2682 0.08464 0.08032 -0.0486 0.9778 0.0520
-7.250 -0.2490 0.06509 0.06063 -0.0740 0.9466 0.0280
-7.000 -0.2335 0.06040 0.05586 -0.0790 0.9357 0.0276
-6.750 -0.2194 0.05471 0.04999 -0.0844 0.9245 0.0272
-6.500 -0.2059 0.04898 0.04401 -0.0888 0.9139 0.0269
-6.250 -0.1947 0.04388 0.03856 -0.0910 0.9022 0.0267
-6.000 -0.1810 0.03904 0.03318 -0.0925 0.8918 0.0274
-5.750 -0.1626 0.03475 0.02816 -0.0934 0.8839 0.0286
-5.500 -0.1441 0.03237 0.02554 -0.0932 0.8745 0.0297
-5.250 -0.1216 0.02989 0.02265 -0.0931 0.8674 0.0303
-5.000 -0.0990 0.02781 0.02017 -0.0926 0.8591 0.0311
-4.750 -0.0741 0.02593 0.01790 -0.0922 0.8525 0.0322
-4.500 -0.0493 0.02457 0.01616 -0.0917 0.8445 0.0349
-4.250 -0.0225 0.02320 0.01439 -0.0911 0.8384 0.0371
-4.000 0.0019 0.02189 0.01298 -0.0906 0.8305 0.0387
-3.750 0.0286 0.02091 0.01187 -0.0901 0.8249 0.0411
-3.500 0.0536 0.02026 0.01108 -0.0895 0.8166 0.0454
-3.250 0.0799 0.01935 0.01006 -0.0889 0.8109 0.0486
-3.000 0.1044 0.01874 0.00942 -0.0883 0.8028 0.0525
-2.750 0.1310 0.01819 0.00873 -0.0877 0.7968 0.0594
-2.500 0.1561 0.01767 0.00820 -0.0872 0.7891 0.0715
-2.250 0.1822 0.01702 0.00763 -0.0867 0.7829 0.1003
-2.000 0.2070 0.01642 0.00735 -0.0863 0.7756 0.1774
-1.750 0.2316 0.01572 0.00720 -0.0859 0.7690 0.3212
-1.500 0.2536 0.01493 0.00716 -0.0847 0.7622 0.5236
-1.250 0.2727 0.01428 0.00715 -0.0820 0.7554 0.7255
-1.000 0.3213 0.01384 0.00688 -0.0845 0.7503 0.9483
-0.750 0.3646 0.01383 0.00663 -0.0877 0.7425 1.0000
-0.500 0.3899 0.01387 0.00644 -0.0870 0.7363 1.0000
-0.250 0.4136 0.01401 0.00643 -0.0863 0.7278 1.0000
0.000 0.4395 0.01406 0.00628 -0.0857 0.7215 1.0000
0.250 0.4638 0.01421 0.00631 -0.0850 0.7129 1.0000
0.500 0.4899 0.01428 0.00622 -0.0845 0.7063 1.0000
0.750 0.5146 0.01442 0.00626 -0.0839 0.6976 1.0000
1.000 0.5407 0.01451 0.00623 -0.0834 0.6904 1.0000
1.250 0.5660 0.01464 0.00626 -0.0829 0.6819 1.0000
1.500 0.5916 0.01476 0.00629 -0.0824 0.6736 1.0000
1.750 0.6177 0.01485 0.00629 -0.0819 0.6654 1.0000
2.000 0.6429 0.01501 0.00639 -0.0813 0.6561 1.0000
2.250 0.6695 0.01509 0.00637 -0.0809 0.6482 1.0000
2.500 0.6945 0.01525 0.00652 -0.0803 0.6382 1.0000
2.750 0.7200 0.01539 0.00662 -0.0798 0.6288 1.0000
3.000 0.7464 0.01549 0.00664 -0.0794 0.6201 1.0000
3.250 0.7712 0.01567 0.00683 -0.0788 0.6093 1.0000
3.500 0.7965 0.01583 0.00698 -0.0783 0.5990 1.0000
3.750 0.8223 0.01596 0.00706 -0.0778 0.5892 1.0000
4.000 0.8473 0.01613 0.00723 -0.0772 0.5779 1.0000
4.250 0.8720 0.01632 0.00743 -0.0766 0.5659 1.0000
4.500 0.8967 0.01650 0.00764 -0.0760 0.5538 1.0000
4.750 0.9213 0.01669 0.00782 -0.0754 0.5412 1.0000
5.000 0.9457 0.01689 0.00802 -0.0747 0.5280 1.0000
5.250 0.9698 0.01711 0.00826 -0.0740 0.5142 1.0000
5.500 0.9934 0.01736 0.00851 -0.0733 0.4997 1.0000
5.750 1.0167 0.01762 0.00878 -0.0725 0.4846 1.0000
6.000 1.0396 0.01792 0.00908 -0.0717 0.4687 1.0000
6.250 1.0620 0.01824 0.00943 -0.0708 0.4524 1.0000
6.500 1.0838 0.01860 0.00978 -0.0698 0.4355 1.0000
6.750 1.1051 0.01899 0.01016 -0.0688 0.4184 1.0000
7.000 1.1257 0.01943 0.01058 -0.0678 0.4008 1.0000
7.250 1.1456 0.01991 0.01110 -0.0666 0.3829 1.0000
7.500 1.1647 0.02043 0.01162 -0.0654 0.3650 1.0000
7.750 1.1831 0.02100 0.01217 -0.0641 0.3476 1.0000
8.000 1.2004 0.02162 0.01277 -0.0627 0.3306 1.0000
8.250 1.2170 0.02228 0.01343 -0.0612 0.3140 1.0000
8.500 1.2328 0.02297 0.01416 -0.0597 0.2980 1.0000
8.750 1.2475 0.02371 0.01492 -0.0580 0.2825 1.0000
9.000 1.2612 0.02450 0.01571 -0.0563 0.2682 1.0000
9.250 1.2728 0.02531 0.01654 -0.0542 0.2546 1.0000
9.500 1.2829 0.02618 0.01744 -0.0520 0.2419 1.0000
9.750 1.2925 0.02713 0.01844 -0.0500 0.2298 1.0000
10.000 1.3023 0.02812 0.01950 -0.0480 0.2179 1.0000
10.250 1.3113 0.02920 0.02064 -0.0462 0.2066 1.0000
10.500 1.3198 0.03036 0.02186 -0.0444 0.1964 1.0000
10.750 1.3265 0.03167 0.02317 -0.0426 0.1866 1.0000
11.000 1.3344 0.03298 0.02460 -0.0411 0.1766 1.0000
11.250 1.3415 0.03440 0.02610 -0.0396 0.1676 1.0000
11.750 1.3528 0.03760 0.02949 -0.0369 0.1508 1.0000
12.000 1.3571 0.03939 0.03134 -0.0357 0.1433 1.0000
12.250 1.3613 0.04125 0.03332 -0.0346 0.1358 1.0000
12.500 1.3653 0.04323 0.03538 -0.0336 0.1291 1.0000
12.750 1.3678 0.04537 0.03764 -0.0328 0.1223 1.0000
13.000 1.3702 0.04761 0.03997 -0.0321 0.1163 1.0000
13.250 1.3717 0.05001 0.04250 -0.0315 0.1102 1.0000
13.500 1.3719 0.05258 0.04515 -0.0310 0.1051 1.0000
13.750 1.3722 0.05529 0.04804 -0.0308 0.0990 1.0000
14.000 1.3683 0.05843 0.05118 -0.0308 0.0942 1.0000
14.250 1.3673 0.06152 0.05455 -0.0309 0.0881 1.0000
14.500 1.3604 0.06534 0.05842 -0.0316 0.0829 1.0000
14.750 1.3559 0.06914 0.06241 -0.0324 0.0767 1.0000
15.000 1.3473 0.07361 0.06697 -0.0337 0.0716 1.0000
15.250 1.3400 0.07815 0.07166 -0.0351 0.0660 1.0000
15.500 1.3302 0.08326 0.07688 -0.0369 0.0612 1.0000
15.750 1.3200 0.08863 0.08237 -0.0390 0.0565 1.0000
16.000 1.3104 0.09407 0.08798 -0.0412 0.0524 1.0000
16.250 1.2976 0.10022 0.09422 -0.0439 0.0495 1.0000
16.500 1.2876 0.10605 0.10019 -0.0465 0.0468 1.0000
16.750 1.2764 0.11229 0.10662 -0.0494 0.0434 1.0000
17.000 1.2634 0.11903 0.11347 -0.0528 0.0409 1.0000
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