S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1221 w/ 4 deg flap (s1221-flap-il) Reynolds number: 50,000 Max Cl/Cd: 39.23 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1221-flap-il-50000-n5.txt Download as CSV file: xf-s1221-flap-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1221 w/ 4 deg flap
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2782 0.10221 0.09586 -0.0243 1.0000 0.0619
-7.000 -0.2794 0.09964 0.09339 -0.0236 1.0000 0.0607
-6.500 -0.3090 0.09232 0.08632 -0.0253 1.0000 0.0545
-6.250 -0.3069 0.08971 0.08380 -0.0247 1.0000 0.0541
-6.000 -0.3054 0.08688 0.08105 -0.0247 1.0000 0.0536
-5.750 -0.3035 0.08391 0.07818 -0.0251 1.0000 0.0529
-5.500 -0.3012 0.08044 0.07480 -0.0266 1.0000 0.0521
-5.250 -0.2971 0.07638 0.07084 -0.0295 1.0000 0.0512
-5.000 -0.2848 0.07070 0.06522 -0.0361 0.9989 0.0501
-4.750 -0.1662 0.04452 0.03758 -0.0922 0.9971 0.0461
-4.500 -0.0919 0.03900 0.03141 -0.1068 0.9912 0.0469
-4.250 -0.0272 0.03566 0.02764 -0.1165 0.9829 0.0488
-4.000 0.0353 0.03303 0.02448 -0.1247 0.9724 0.0531
-3.750 0.0898 0.03101 0.02225 -0.1303 0.9593 0.0572
-3.500 0.1421 0.02932 0.02038 -0.1349 0.9440 0.0618
-3.250 0.1969 0.02765 0.01865 -0.1404 0.9263 0.0721
-3.000 0.2522 0.02582 0.01685 -0.1464 0.9018 0.0935
-2.750 0.3145 0.02429 0.01629 -0.1544 0.8671 0.2708
-2.500 0.3367 0.02499 0.01703 -0.1520 0.8033 0.3363
-2.250 0.3858 0.02508 0.01691 -0.1527 0.7622 0.3890
-2.000 0.4668 0.02423 0.01522 -0.1610 0.7189 0.4160
-1.750 0.5244 0.02404 0.01431 -0.1661 0.6763 0.4312
-1.500 0.5614 0.02417 0.01403 -0.1673 0.6441 0.4403
-1.250 0.5999 0.02425 0.01370 -0.1695 0.6174 0.4503
-1.000 0.6325 0.02442 0.01357 -0.1702 0.5965 0.4585
-0.750 0.6684 0.02457 0.01339 -0.1718 0.5783 0.4678
-0.500 0.7010 0.02475 0.01334 -0.1727 0.5627 0.4758
-0.250 0.7354 0.02495 0.01330 -0.1740 0.5490 0.4857
0.000 0.7686 0.02517 0.01333 -0.1749 0.5372 0.4958
0.250 0.8014 0.02540 0.01340 -0.1758 0.5258 0.5055
0.500 0.8350 0.02565 0.01352 -0.1770 0.5152 0.5175
0.750 0.8674 0.02592 0.01366 -0.1777 0.5065 0.5298
1.000 0.8986 0.02620 0.01395 -0.1784 0.4975 0.5430
1.250 0.9308 0.02651 0.01417 -0.1791 0.4900 0.5578
1.500 0.9609 0.02685 0.01454 -0.1795 0.4821 0.5742
1.750 0.9907 0.02720 0.01490 -0.1797 0.4749 0.5931
2.000 1.0202 0.02758 0.01529 -0.1800 0.4686 0.6147
2.250 1.0473 0.02800 0.01583 -0.1797 0.4620 0.6378
2.500 1.0742 0.02840 0.01631 -0.1793 0.4565 0.6645
2.750 1.0998 0.02885 0.01683 -0.1787 0.4512 0.6956
3.000 1.1240 0.02933 0.01746 -0.1779 0.4451 0.7328
3.250 1.1490 0.02975 0.01793 -0.1772 0.4400 0.7778
3.500 1.1711 0.03003 0.01825 -0.1758 0.4361 0.8285
3.750 1.1835 0.03019 0.01870 -0.1727 0.4311 1.0000
4.000 1.2159 0.03104 0.01951 -0.1741 0.4255 1.0000
4.250 1.2478 0.03181 0.02017 -0.1751 0.4209 1.0000
4.500 1.2762 0.03273 0.02115 -0.1756 0.4162 1.0000
4.750 1.3024 0.03373 0.02225 -0.1757 0.4110 1.0000
5.000 1.3299 0.03460 0.02314 -0.1759 0.4064 1.0000
5.250 1.3591 0.03539 0.02389 -0.1762 0.4026 1.0000
5.500 1.3812 0.03661 0.02532 -0.1757 0.3975 1.0000
5.750 1.4044 0.03775 0.02661 -0.1753 0.3927 1.0000
6.000 1.4300 0.03870 0.02764 -0.1751 0.3885 1.0000
6.250 1.4583 0.03951 0.02840 -0.1752 0.3850 1.0000
6.500 1.4735 0.04117 0.03042 -0.1738 0.3793 1.0000
6.750 1.4942 0.04244 0.03186 -0.1731 0.3744 1.0000
7.000 1.5193 0.04336 0.03284 -0.1727 0.3704 1.0000
7.250 1.5392 0.04468 0.03433 -0.1718 0.3657 1.0000
7.500 1.5516 0.04654 0.03650 -0.1702 0.3600 1.0000
7.750 1.5729 0.04764 0.03774 -0.1693 0.3552 1.0000
8.000 1.6014 0.04820 0.03828 -0.1692 0.3513 1.0000
8.250 1.6001 0.05105 0.04160 -0.1662 0.3446 1.0000
8.500 1.6169 0.05235 0.04307 -0.1649 0.3393 1.0000
8.750 1.6479 0.05253 0.04325 -0.1649 0.3351 1.0000
9.000 1.6341 0.05626 0.04746 -0.1609 0.3281 1.0000
9.250 1.6481 0.05760 0.04896 -0.1593 0.3225 1.0000
9.500 1.6770 0.05773 0.04915 -0.1589 0.3179 1.0000
9.750 1.6394 0.06317 0.05505 -0.1533 0.3110 1.0000
10.000 1.6539 0.06421 0.05624 -0.1516 0.3056 1.0000
10.250 1.6606 0.06581 0.05798 -0.1494 0.3006 1.0000
10.500 1.4840 0.08722 0.07974 -0.1449 0.2919 1.0000
10.750 1.5422 0.08241 0.07504 -0.1422 0.2886 1.0000
11.000 1.4112 0.10762 0.10034 -0.1519 0.2730 1.0000
11.250 1.4502 0.10407 0.09692 -0.1484 0.2708 1.0000
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Polar data table (+)
Polar graphs
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