S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: S1221 w/ 4 deg flap (s1221-flap-il) Reynolds number: 100,000 Max Cl/Cd: 48.32 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1221-flap-il-100000.txt Download as CSV file: xf-s1221-flap-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.2809 0.09918 0.09507 -0.0151 1.0000 0.1152
-6.250 -0.3153 0.09967 0.09573 -0.0161 1.0000 0.1176
-6.000 -0.3132 0.09591 0.09206 -0.0149 1.0000 0.1193
-5.750 -0.2969 0.09310 0.08927 -0.0110 1.0000 0.1221
-5.500 -0.2938 0.09111 0.08736 -0.0095 1.0000 0.1260
-5.250 -0.3107 0.08850 0.08492 -0.0224 1.0000 0.1337
-5.000 -0.3061 0.08611 0.08260 -0.0145 1.0000 0.1352
-4.750 -0.2947 0.08415 0.08070 -0.0115 0.9988 0.1384
-4.500 -0.2159 0.07614 0.07260 -0.0458 0.9820 0.1644
-4.250 -0.1926 0.07298 0.06949 -0.0395 0.9728 0.1665
-4.000 0.0422 0.03059 0.02390 -0.1304 0.9919 0.0647
-3.750 0.1166 0.02764 0.02042 -0.1398 0.9847 0.0646
-3.500 0.1831 0.02493 0.01757 -0.1470 0.9750 0.0659
-3.250 0.2459 0.02303 0.01577 -0.1531 0.9608 0.0704
-3.000 0.3154 0.02117 0.01400 -0.1604 0.9438 0.0845
-2.750 0.4000 0.01935 0.01305 -0.1708 0.9159 0.3314
-2.500 0.4278 0.01960 0.01348 -0.1680 0.8515 0.3817
-2.250 0.5196 0.01903 0.01242 -0.1762 0.7516 0.4324
-2.000 0.5909 0.01929 0.01179 -0.1839 0.6809 0.4506
-1.750 0.6280 0.01961 0.01170 -0.1854 0.6450 0.4609
-1.500 0.6631 0.01972 0.01148 -0.1869 0.6179 0.4697
-1.250 0.6964 0.01988 0.01134 -0.1879 0.5974 0.4782
-1.000 0.7303 0.02000 0.01120 -0.1892 0.5803 0.4860
-0.750 0.7613 0.02018 0.01120 -0.1898 0.5660 0.4935
-0.500 0.7955 0.02034 0.01111 -0.1913 0.5531 0.5012
-0.250 0.8256 0.02057 0.01119 -0.1916 0.5418 0.5088
0.000 0.8580 0.02076 0.01126 -0.1926 0.5306 0.5181
0.250 0.8885 0.02105 0.01141 -0.1930 0.5222 0.5261
0.500 0.9196 0.02127 0.01160 -0.1938 0.5131 0.5360
0.750 0.9506 0.02164 0.01181 -0.1943 0.5060 0.5474
1.000 0.9788 0.02189 0.01216 -0.1943 0.4979 0.5589
1.250 1.0093 0.02221 0.01241 -0.1948 0.4910 0.5726
1.500 1.0389 0.02260 0.01281 -0.1951 0.4848 0.5877
1.750 1.0674 0.02295 0.01325 -0.1952 0.4785 0.6049
2.000 1.0960 0.02335 0.01363 -0.1952 0.4732 0.6250
2.250 1.1233 0.02382 0.01420 -0.1949 0.4677 0.6484
2.500 1.1487 0.02424 0.01477 -0.1943 0.4619 0.6736
2.750 1.1750 0.02471 0.01528 -0.1937 0.4573 0.7043
3.000 1.2007 0.02530 0.01586 -0.1930 0.4534 0.7395
3.250 1.2225 0.02573 0.01657 -0.1917 0.4484 0.7801
3.500 1.2437 0.02601 0.01699 -0.1902 0.4435 0.8308
4.000 1.2881 0.02666 0.01768 -0.1879 0.4361 1.0000
4.250 1.3175 0.02757 0.01875 -0.1887 0.4312 1.0000
4.500 1.3468 0.02837 0.01958 -0.1893 0.4262 1.0000
4.750 1.3765 0.02911 0.02025 -0.1898 0.4219 1.0000
5.000 1.4051 0.03007 0.02121 -0.1901 0.4182 1.0000
5.250 1.4281 0.03114 0.02251 -0.1896 0.4132 1.0000
5.500 1.4541 0.03200 0.02344 -0.1894 0.4084 1.0000
5.750 1.4822 0.03273 0.02415 -0.1894 0.4043 1.0000
6.000 1.5068 0.03385 0.02536 -0.1891 0.4001 1.0000
6.250 1.5269 0.03507 0.02683 -0.1881 0.3945 1.0000
6.500 1.5527 0.03586 0.02768 -0.1878 0.3898 1.0000
6.750 1.5817 0.03652 0.02826 -0.1879 0.3857 1.0000
7.000 1.5971 0.03813 0.03022 -0.1863 0.3798 1.0000
7.250 1.6195 0.03905 0.03127 -0.1855 0.3742 1.0000
7.500 1.6489 0.03943 0.03158 -0.1855 0.3697 1.0000
7.750 1.6636 0.04110 0.03355 -0.1838 0.3637 1.0000
8.000 1.6836 0.04210 0.03473 -0.1827 0.3576 1.0000
8.250 1.7147 0.04217 0.03470 -0.1828 0.3528 1.0000
8.500 1.7250 0.04408 0.03696 -0.1806 0.3462 1.0000
8.750 1.7475 0.04465 0.03763 -0.1796 0.3398 1.0000
9.000 1.7843 0.04414 0.03691 -0.1804 0.3349 1.0000
9.250 1.7844 0.04640 0.03969 -0.1768 0.3266 1.0000
9.500 1.8196 0.04543 0.03856 -0.1771 0.3203 1.0000
9.750 1.8274 0.04698 0.04045 -0.1743 0.3124 1.0000
10.000 1.8576 0.04614 0.03954 -0.1740 0.3052 1.0000
10.250 1.8707 0.04695 0.04056 -0.1717 0.2973 1.0000
10.500 1.8976 0.04611 0.03970 -0.1709 0.2892 1.0000
10.750 1.9090 0.04678 0.04057 -0.1683 0.2809 1.0000
11.000 1.9365 0.04568 0.03939 -0.1675 0.2725 1.0000
11.250 1.9391 0.04681 0.04082 -0.1638 0.2636 1.0000
11.500 1.9690 0.04542 0.03925 -0.1632 0.2549 1.0000
11.750 1.9600 0.04706 0.04130 -0.1580 0.2458 1.0000
12.000 1.9689 0.04718 0.04146 -0.1549 0.2371 1.0000
12.250 1.9666 0.04785 0.04224 -0.1503 0.2284 1.0000
12.500 1.9566 0.04945 0.04404 -0.1454 0.2201 1.0000
12.750 1.9589 0.05009 0.04462 -0.1420 0.2107 1.0000
13.000 1.9418 0.05286 0.04765 -0.1375 0.2019 1.0000
13.250 1.9316 0.05541 0.05026 -0.1343 0.1930 1.0000
13.500 1.9263 0.05766 0.05240 -0.1318 0.1834 1.0000
13.750 1.9015 0.06265 0.05770 -0.1296 0.1759 1.0000
14.000 1.8901 0.06647 0.06149 -0.1284 0.1677 1.0000
14.250 1.8681 0.07223 0.06741 -0.1283 0.1607 1.0000
14.500 1.8550 0.07720 0.07239 -0.1285 0.1533 1.0000
14.750 1.8358 0.08345 0.07877 -0.1298 0.1468 1.0000
15.000 1.8273 0.08827 0.08357 -0.1305 0.1401 1.0000
15.250 1.8081 0.09512 0.09058 -0.1326 0.1346 1.0000
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