S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1221 w/ 4 deg flap (s1221-flap-il) Reynolds number: 100,000 Max Cl/Cd: 56.39 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1221-flap-il-100000-n5.txt Download as CSV file: xf-s1221-flap-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.1982 0.08708 0.08290 -0.0298 0.9925 0.0372
-7.250 -0.1853 0.08211 0.07794 -0.0334 0.9877 0.0352
-6.750 -0.3033 0.08815 0.08382 -0.0253 0.9969 0.0323
-6.500 -0.2828 0.08477 0.08044 -0.0292 0.9910 0.0317
-6.250 -0.2634 0.08014 0.07583 -0.0350 0.9841 0.0308
-5.750 -0.2208 0.05272 0.04817 -0.0747 0.9672 0.0268
-5.500 -0.1166 0.03630 0.03050 -0.1164 0.9632 0.0262
-5.250 -0.0431 0.03095 0.02431 -0.1307 0.9583 0.0266
-5.000 0.0137 0.02813 0.02104 -0.1384 0.9514 0.0282
-4.750 0.0646 0.02623 0.01893 -0.1438 0.9431 0.0301
-4.500 0.1086 0.02445 0.01691 -0.1471 0.9323 0.0311
-4.250 0.1516 0.02298 0.01528 -0.1499 0.9203 0.0321
-4.000 0.1917 0.02175 0.01405 -0.1521 0.9048 0.0335
-3.750 0.2273 0.02081 0.01311 -0.1536 0.8813 0.0354
-3.500 0.2553 0.02016 0.01238 -0.1537 0.8352 0.0381
-3.000 0.4751 0.01638 0.00804 -0.1864 0.6572 0.2889
-2.750 0.5074 0.01721 0.00857 -0.1867 0.6139 0.3322
-2.500 0.5384 0.01761 0.00868 -0.1870 0.5826 0.3505
-2.250 0.5717 0.01781 0.00850 -0.1879 0.5584 0.3622
-2.000 0.6020 0.01794 0.00845 -0.1881 0.5392 0.3691
-1.750 0.6340 0.01806 0.00830 -0.1887 0.5225 0.3770
-1.500 0.6650 0.01817 0.00821 -0.1892 0.5078 0.3832
-1.250 0.6954 0.01827 0.00816 -0.1895 0.4949 0.3890
-1.000 0.7267 0.01841 0.00808 -0.1901 0.4837 0.3958
-0.750 0.7561 0.01855 0.00811 -0.1902 0.4738 0.4016
-0.500 0.7859 0.01870 0.00816 -0.1904 0.4650 0.4082
-0.250 0.8159 0.01887 0.00819 -0.1908 0.4568 0.4150
0.000 0.8451 0.01904 0.00830 -0.1908 0.4492 0.4214
0.250 0.8747 0.01923 0.00840 -0.1911 0.4415 0.4303
0.500 0.9037 0.01946 0.00856 -0.1912 0.4351 0.4383
0.750 0.9334 0.01965 0.00872 -0.1914 0.4282 0.4484
1.000 0.9622 0.01987 0.00892 -0.1914 0.4226 0.4573
1.250 0.9913 0.02014 0.00913 -0.1916 0.4176 0.4684
1.500 1.0202 0.02037 0.00940 -0.1916 0.4117 0.4815
1.750 1.0485 0.02062 0.00965 -0.1916 0.4064 0.4954
2.250 1.1050 0.02118 0.01026 -0.1915 0.3971 0.5290
2.500 1.1332 0.02146 0.01061 -0.1914 0.3925 0.5488
2.750 1.1609 0.02176 0.01094 -0.1912 0.3884 0.5716
3.000 1.1885 0.02210 0.01128 -0.1910 0.3847 0.5991
3.250 1.2149 0.02238 0.01178 -0.1906 0.3801 0.6298
3.500 1.2407 0.02270 0.01223 -0.1899 0.3760 0.6646
3.750 1.2663 0.02304 0.01265 -0.1893 0.3725 0.7048
4.000 1.2921 0.02341 0.01305 -0.1887 0.3693 0.7462
4.250 1.3179 0.02379 0.01352 -0.1881 0.3656 0.7859
4.500 1.3407 0.02406 0.01395 -0.1869 0.3616 0.8228
4.750 1.3576 0.02417 0.01422 -0.1844 0.3583 0.8808
5.000 1.3826 0.02452 0.01462 -0.1838 0.3552 1.0000
5.250 1.4115 0.02505 0.01507 -0.1841 0.3522 1.0000
5.500 1.4386 0.02560 0.01572 -0.1840 0.3484 1.0000
5.750 1.4651 0.02616 0.01640 -0.1838 0.3444 1.0000
6.000 1.4919 0.02670 0.01700 -0.1836 0.3408 1.0000
6.250 1.5188 0.02722 0.01752 -0.1835 0.3374 1.0000
6.500 1.5457 0.02777 0.01809 -0.1833 0.3341 1.0000
6.750 1.5695 0.02841 0.01894 -0.1827 0.3296 1.0000
7.000 1.5942 0.02897 0.01962 -0.1822 0.3253 1.0000
7.250 1.6196 0.02947 0.02016 -0.1817 0.3214 1.0000
7.500 1.6449 0.03000 0.02072 -0.1813 0.3176 1.0000
7.750 1.6663 0.03068 0.02166 -0.1802 0.3123 1.0000
8.000 1.6895 0.03121 0.02231 -0.1794 0.3075 1.0000
8.250 1.7142 0.03164 0.02274 -0.1789 0.3035 1.0000
8.500 1.7346 0.03237 0.02370 -0.1777 0.2984 1.0000
8.750 1.7552 0.03299 0.02452 -0.1765 0.2929 1.0000
9.000 1.7779 0.03340 0.02497 -0.1756 0.2882 1.0000
9.250 1.7964 0.03409 0.02587 -0.1741 0.2824 1.0000
9.500 1.8144 0.03468 0.02664 -0.1725 0.2759 1.0000
9.750 1.8346 0.03501 0.02699 -0.1711 0.2703 1.0000
10.000 1.8478 0.03586 0.02819 -0.1689 0.2625 1.0000
10.250 1.8643 0.03627 0.02866 -0.1670 0.2560 1.0000
10.500 1.8757 0.03717 0.02985 -0.1646 0.2477 1.0000
10.750 1.8882 0.03771 0.03047 -0.1621 0.2405 1.0000
11.000 1.8954 0.03879 0.03184 -0.1591 0.2313 1.0000
11.250 1.9006 0.03972 0.03288 -0.1557 0.2236 1.0000
11.500 1.9039 0.04092 0.03427 -0.1523 0.2146 1.0000
11.750 1.9058 0.04233 0.03584 -0.1490 0.2057 1.0000
12.000 1.9051 0.04392 0.03751 -0.1456 0.1973 1.0000
12.250 1.9025 0.04602 0.03980 -0.1425 0.1876 1.0000
12.500 1.8967 0.04846 0.04237 -0.1395 0.1790 1.0000
12.750 1.8871 0.05146 0.04547 -0.1367 0.1708 1.0000
13.000 1.8747 0.05512 0.04930 -0.1346 0.1629 1.0000
13.250 1.8566 0.05975 0.05402 -0.1332 0.1565 1.0000
13.500 1.8359 0.06548 0.05996 -0.1332 0.1505 1.0000
13.750 1.8100 0.07273 0.06737 -0.1347 0.1457 1.0000
14.000 1.7813 0.08113 0.07591 -0.1374 0.1415 1.0000
14.250 1.7513 0.09035 0.08533 -0.1408 0.1369 1.0000
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Polar data table (+)
Polar graphs
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