S4061-096-84 (s4061-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4061-096-84 (s4061-il) Reynolds number: 50,000 Max Cl/Cd: 39.08 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4061-il-50000-n5.txt Download as CSV file: xf-s4061-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4061-096-84
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3392 0.09589 0.08927 -0.0414 1.0000 0.0493
-8.250 -0.3381 0.09282 0.08629 -0.0418 1.0000 0.0491
-8.000 -0.3377 0.09004 0.08361 -0.0414 1.0000 0.0487
-7.750 -0.3443 0.08764 0.08134 -0.0407 1.0000 0.0485
-7.500 -0.3534 0.08566 0.07950 -0.0393 1.0000 0.0482
-7.250 -0.3634 0.08361 0.07756 -0.0380 1.0000 0.0478
-7.000 -0.3744 0.08149 0.07555 -0.0369 1.0000 0.0475
-6.750 -0.3847 0.07910 0.07323 -0.0362 1.0000 0.0472
-6.500 -0.3924 0.07653 0.07072 -0.0359 1.0000 0.0467
-6.250 -0.3827 0.07170 0.06586 -0.0410 0.9948 0.0463
-6.000 -0.3588 0.06520 0.05922 -0.0495 0.9856 0.0456
-5.750 -0.3345 0.05857 0.05235 -0.0574 0.9766 0.0448
-5.500 -0.3075 0.05200 0.04539 -0.0647 0.9683 0.0442
-5.250 -0.2772 0.04598 0.03882 -0.0709 0.9610 0.0441
-5.000 -0.2477 0.04104 0.03325 -0.0750 0.9535 0.0446
-4.750 -0.2136 0.03685 0.02833 -0.0786 0.9473 0.0464
-4.500 -0.1810 0.03364 0.02433 -0.0807 0.9408 0.0498
-4.250 -0.1489 0.03187 0.02236 -0.0824 0.9343 0.0543
-4.000 -0.1123 0.02967 0.01956 -0.0842 0.9292 0.0597
-3.750 -0.0832 0.02843 0.01819 -0.0848 0.9215 0.0691
-3.500 -0.0456 0.02706 0.01657 -0.0867 0.9166 0.0875
-3.250 -0.0171 0.02621 0.01565 -0.0871 0.9087 0.1143
-3.000 0.0172 0.02536 0.01482 -0.0885 0.9028 0.1507
-2.750 0.0466 0.02475 0.01416 -0.0890 0.8952 0.1909
-2.500 0.0794 0.02416 0.01364 -0.0901 0.8886 0.2390
-2.250 0.1082 0.02370 0.01326 -0.0904 0.8811 0.2940
-2.000 0.1382 0.02321 0.01298 -0.0910 0.8741 0.3646
-1.750 0.1648 0.02273 0.01282 -0.0907 0.8666 0.4574
-1.500 0.1884 0.02215 0.01274 -0.0894 0.8592 0.5917
-1.250 0.2307 0.02114 0.01240 -0.0902 0.8543 1.0000
-1.000 0.2568 0.02141 0.01229 -0.0902 0.8450 1.0000
-0.750 0.2870 0.02162 0.01215 -0.0907 0.8376 1.0000
-0.500 0.3144 0.02186 0.01213 -0.0907 0.8290 1.0000
-0.250 0.3419 0.02212 0.01215 -0.0907 0.8208 1.0000
0.000 0.3706 0.02235 0.01215 -0.0909 0.8129 1.0000
0.250 0.3958 0.02266 0.01229 -0.0905 0.8040 1.0000
0.500 0.4259 0.02284 0.01230 -0.0907 0.7968 1.0000
0.750 0.4493 0.02320 0.01254 -0.0901 0.7871 1.0000
1.000 0.4806 0.02333 0.01254 -0.0904 0.7806 1.0000
1.250 0.5028 0.02374 0.01287 -0.0897 0.7702 1.0000
1.500 0.5322 0.02391 0.01295 -0.0897 0.7631 1.0000
1.750 0.5563 0.02426 0.01325 -0.0891 0.7533 1.0000
2.000 0.5811 0.02459 0.01353 -0.0885 0.7441 1.0000
2.250 0.6101 0.02473 0.01363 -0.0884 0.7364 1.0000
2.500 0.6328 0.02514 0.01404 -0.0876 0.7257 1.0000
2.750 0.6616 0.02526 0.01415 -0.0873 0.7179 1.0000
3.000 0.6862 0.02556 0.01446 -0.0867 0.7076 1.0000
3.250 0.7097 0.02590 0.01483 -0.0859 0.6967 1.0000
3.500 0.7390 0.02592 0.01489 -0.0855 0.6882 1.0000
3.750 0.7638 0.02613 0.01515 -0.0847 0.6771 1.0000
4.000 0.7873 0.02642 0.01549 -0.0838 0.6649 1.0000
4.250 0.8123 0.02658 0.01575 -0.0829 0.6533 1.0000
4.500 0.8397 0.02657 0.01581 -0.0822 0.6423 1.0000
4.750 0.8676 0.02651 0.01582 -0.0814 0.6309 1.0000
5.000 0.8913 0.02670 0.01610 -0.0804 0.6172 1.0000
5.250 0.9154 0.02684 0.01638 -0.0793 0.6031 1.0000
5.500 0.9398 0.02694 0.01658 -0.0782 0.5886 1.0000
5.750 0.9644 0.02701 0.01676 -0.0771 0.5734 1.0000
6.000 0.9892 0.02705 0.01694 -0.0760 0.5576 1.0000
6.250 1.0133 0.02713 0.01712 -0.0747 0.5405 1.0000
6.500 1.0337 0.02745 0.01759 -0.0733 0.5209 1.0000
6.750 1.0562 0.02761 0.01785 -0.0719 0.5009 1.0000
7.000 1.0783 0.02780 0.01815 -0.0705 0.4796 1.0000
7.250 1.0981 0.02815 0.01860 -0.0689 0.4562 1.0000
7.500 1.1170 0.02858 0.01910 -0.0673 0.4313 1.0000
7.750 1.1354 0.02906 0.01960 -0.0655 0.4057 1.0000
8.000 1.1520 0.02969 0.02026 -0.0637 0.3793 1.0000
8.250 1.1659 0.03054 0.02113 -0.0618 0.3521 1.0000
8.500 1.1783 0.03152 0.02210 -0.0598 0.3257 1.0000
8.750 1.1893 0.03262 0.02318 -0.0578 0.3005 1.0000
9.000 1.1984 0.03385 0.02435 -0.0556 0.2772 1.0000
9.250 1.2047 0.03524 0.02575 -0.0534 0.2549 1.0000
9.500 1.2101 0.03674 0.02724 -0.0511 0.2347 1.0000
9.750 1.2146 0.03842 0.02894 -0.0491 0.2152 1.0000
10.000 1.2188 0.04024 0.03079 -0.0473 0.1969 1.0000
10.250 1.2219 0.04219 0.03276 -0.0456 0.1800 1.0000
10.500 1.2247 0.04429 0.03488 -0.0441 0.1645 1.0000
10.750 1.2266 0.04655 0.03716 -0.0428 0.1500 1.0000
11.000 1.2282 0.04896 0.03962 -0.0416 0.1364 1.0000
11.250 1.2287 0.05157 0.04232 -0.0406 0.1236 1.0000
11.500 1.2283 0.05438 0.04521 -0.0398 0.1117 1.0000
11.750 1.2267 0.05739 0.04831 -0.0392 0.1009 1.0000
12.000 1.2242 0.06059 0.05157 -0.0389 0.0914 1.0000
12.250 1.2208 0.06389 0.05483 -0.0388 0.0838 1.0000
12.500 1.2193 0.06743 0.05862 -0.0387 0.0759 1.0000
12.750 1.2166 0.07100 0.06220 -0.0389 0.0702 1.0000
13.000 1.2146 0.07482 0.06628 -0.0391 0.0647 1.0000
13.250 1.2128 0.07835 0.06976 -0.0394 0.0607 1.0000
13.500 1.2094 0.08282 0.07458 -0.0400 0.0570 1.0000
13.750 1.2058 0.08725 0.07924 -0.0407 0.0542 1.0000
14.000 1.2030 0.09146 0.08358 -0.0416 0.0520 1.0000
14.250 1.2027 0.09534 0.08751 -0.0423 0.0499 1.0000
14.500 1.1902 0.10177 0.09430 -0.0448 0.0488 1.0000
14.750 1.1758 0.10881 0.10164 -0.0480 0.0481 1.0000
15.000 1.1587 0.11680 0.10990 -0.0522 0.0477 1.0000
15.250 1.1385 0.12603 0.11934 -0.0575 0.0478 1.0000
15.500 1.1160 0.13664 0.13014 -0.0638 0.0482 1.0000
15.750 1.0917 0.14881 0.14241 -0.0712 0.0488 1.0000
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Polar data table (+)
Polar graphs
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