S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1221 w/ 4 deg flap (s1221-flap-il) Reynolds number: 200,000 Max Cl/Cd: 69.35 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1221-flap-il-200000.txt Download as CSV file: xf-s1221-flap-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2226 0.09616 0.09334 -0.0175 1.0000 0.0521
-7.500 -0.2372 0.09307 0.09030 -0.0193 1.0000 0.0539
-7.250 -0.2512 0.08865 0.08593 -0.0250 0.9976 0.0545
-7.000 -0.2041 0.08403 0.08129 -0.0251 0.9940 0.0567
-6.750 -0.1811 0.08012 0.07737 -0.0290 0.9886 0.0607
-6.500 -0.1930 0.07488 0.07217 -0.0376 0.9806 0.0642
-6.250 -0.1731 0.06913 0.06645 -0.0406 0.9752 0.0659
-6.000 -0.1391 0.06576 0.06306 -0.0426 0.9691 0.0685
-5.750 -0.1249 0.06172 0.05904 -0.0463 0.9603 0.0720
-5.500 -0.2199 0.07409 0.07127 -0.0432 0.9767 0.0669
-5.250 -0.1868 0.07074 0.06791 -0.0479 0.9688 0.0703
-5.000 -0.1455 0.06083 0.05799 -0.0684 0.9590 0.0784
-4.750 0.0648 0.02638 0.02068 -0.1460 0.9676 0.0386
-4.500 0.1219 0.02296 0.01704 -0.1525 0.9616 0.0370
-4.250 0.1870 0.02051 0.01427 -0.1597 0.9558 0.0365
-4.000 0.2381 0.01878 0.01239 -0.1637 0.9452 0.0371
-3.750 0.2889 0.01722 0.01081 -0.1678 0.9335 0.0399
-3.500 0.3394 0.01580 0.00945 -0.1716 0.9171 0.0431
-3.250 0.3894 0.01441 0.00805 -0.1753 0.8882 0.0470
-3.000 0.5518 0.01238 0.00544 -0.2023 0.6779 0.3105
-2.750 0.5751 0.01334 0.00610 -0.2008 0.6192 0.3398
-2.500 0.5993 0.01407 0.00654 -0.1996 0.5827 0.3632
-2.250 0.6242 0.01447 0.00676 -0.1986 0.5576 0.3749
-2.000 0.6522 0.01468 0.00674 -0.1985 0.5375 0.3830
-1.750 0.6801 0.01489 0.00678 -0.1983 0.5213 0.3899
-1.500 0.7099 0.01510 0.00671 -0.1985 0.5071 0.3968
-1.250 0.7384 0.01516 0.00672 -0.1985 0.4944 0.4019
-1.000 0.7674 0.01534 0.00676 -0.1985 0.4835 0.4078
-0.750 0.7975 0.01552 0.00674 -0.1989 0.4736 0.4140
-0.500 0.8266 0.01561 0.00681 -0.1990 0.4648 0.4188
-0.250 0.8558 0.01578 0.00688 -0.1991 0.4569 0.4250
0.000 0.8858 0.01598 0.00697 -0.1994 0.4498 0.4325
0.250 0.9146 0.01610 0.00709 -0.1994 0.4425 0.4389
0.500 0.9446 0.01640 0.00722 -0.1997 0.4363 0.4472
0.750 0.9732 0.01648 0.00738 -0.1997 0.4300 0.4549
1.000 1.0026 0.01667 0.00753 -0.1998 0.4245 0.4654
1.250 1.0320 0.01695 0.00777 -0.2000 0.4197 0.4760
1.500 1.0608 0.01711 0.00801 -0.2001 0.4145 0.4887
1.750 1.0898 0.01729 0.00822 -0.2001 0.4093 0.5032
2.000 1.1190 0.01753 0.00845 -0.2003 0.4050 0.5199
2.250 1.1487 0.01787 0.00881 -0.2006 0.4011 0.5391
2.500 1.1773 0.01805 0.00914 -0.2006 0.3969 0.5620
2.750 1.2060 0.01826 0.00946 -0.2006 0.3926 0.5895
3.000 1.2347 0.01850 0.00978 -0.2006 0.3887 0.6228
3.250 1.2634 0.01892 0.01024 -0.2006 0.3851 0.6617
3.500 1.2895 0.01916 0.01070 -0.2000 0.3817 0.7054
3.750 1.3153 0.01946 0.01115 -0.1993 0.3781 0.7485
4.000 1.3416 0.01975 0.01149 -0.1988 0.3745 0.7898
4.250 1.3664 0.01997 0.01174 -0.1979 0.3712 0.8280
4.500 1.3869 0.02025 0.01204 -0.1961 0.3683 0.8761
4.750 1.4059 0.02034 0.01234 -0.1941 0.3653 1.0000
5.000 1.4345 0.02075 0.01280 -0.1943 0.3615 1.0000
5.250 1.4630 0.02113 0.01319 -0.1944 0.3577 1.0000
5.500 1.4917 0.02155 0.01357 -0.1946 0.3543 1.0000
5.750 1.5207 0.02217 0.01413 -0.1948 0.3509 1.0000
6.000 1.5461 0.02253 0.01465 -0.1943 0.3469 1.0000
6.250 1.5724 0.02290 0.01511 -0.1940 0.3426 1.0000
6.500 1.5995 0.02325 0.01544 -0.1938 0.3386 1.0000
6.750 1.6281 0.02385 0.01593 -0.1940 0.3348 1.0000
7.000 1.6513 0.02419 0.01651 -0.1930 0.3305 1.0000
7.250 1.6762 0.02455 0.01697 -0.1924 0.3259 1.0000
7.500 1.7025 0.02487 0.01728 -0.1921 0.3219 1.0000
7.750 1.7294 0.02542 0.01780 -0.1920 0.3179 1.0000
8.000 1.7510 0.02576 0.01839 -0.1907 0.3127 1.0000
8.250 1.7750 0.02599 0.01866 -0.1899 0.3075 1.0000
8.500 1.8016 0.02633 0.01890 -0.1897 0.3027 1.0000
8.750 1.8210 0.02664 0.01949 -0.1881 0.2967 1.0000
9.000 1.8433 0.02676 0.01965 -0.1870 0.2906 1.0000
9.250 1.8660 0.02706 0.01996 -0.1860 0.2848 1.0000
9.500 1.8847 0.02729 0.02040 -0.1843 0.2779 1.0000
9.750 1.9063 0.02749 0.02058 -0.1831 0.2720 1.0000
10.000 1.9244 0.02789 0.02119 -0.1814 0.2654 1.0000
10.250 1.9427 0.02813 0.02154 -0.1796 0.2585 1.0000
10.500 1.9599 0.02852 0.02206 -0.1777 0.2513 1.0000
10.750 1.9755 0.02885 0.02252 -0.1755 0.2432 1.0000
11.000 1.9899 0.02934 0.02316 -0.1732 0.2344 1.0000
11.250 2.0013 0.02988 0.02374 -0.1704 0.2254 1.0000
11.500 2.0100 0.03057 0.02459 -0.1672 0.2145 1.0000
11.750 2.0167 0.03143 0.02556 -0.1638 0.2031 1.0000
12.000 2.0211 0.03256 0.02674 -0.1602 0.1907 1.0000
12.250 2.0227 0.03402 0.02823 -0.1566 0.1774 1.0000
12.500 2.0210 0.03586 0.03009 -0.1528 0.1640 1.0000
12.750 2.0157 0.03813 0.03240 -0.1489 0.1517 1.0000
13.000 2.0063 0.04091 0.03520 -0.1451 0.1410 1.0000
13.250 1.9954 0.04409 0.03843 -0.1417 0.1314 1.0000
13.500 1.9833 0.04766 0.04211 -0.1389 0.1230 1.0000
13.750 1.9645 0.05226 0.04675 -0.1367 0.1172 1.0000
14.000 1.9503 0.05692 0.05158 -0.1357 0.1108 1.0000
14.250 1.9293 0.06309 0.05784 -0.1360 0.1064 1.0000
14.500 1.9085 0.06985 0.06472 -0.1372 0.1023 1.0000
14.750 1.8911 0.07653 0.07158 -0.1389 0.0979 1.0000
15.000 1.8708 0.08380 0.07893 -0.1410 0.0946 1.0000
15.250 1.8510 0.09095 0.08611 -0.1429 0.0912 1.0000
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Polar data table (+)
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