S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1221 w/ 4 deg flap (s1221-flap-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.83 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1221-flap-il-1000000.txt Download as CSV file: xf-s1221-flap-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1843 0.10088 0.09916 -0.0587 0.9845 0.0128
-9.500 -0.1735 0.09813 0.09641 -0.0601 0.9820 0.0130
-9.250 -0.1613 0.09458 0.09287 -0.0630 0.9801 0.0130
-9.000 -0.1473 0.09128 0.08957 -0.0659 0.9786 0.0132
-8.750 -0.1307 0.08788 0.08617 -0.0695 0.9773 0.0136
-8.500 -0.1269 0.08487 0.08318 -0.0701 0.9719 0.0137
-8.250 -0.1155 0.08098 0.07929 -0.0734 0.9695 0.0142
-8.000 -0.1137 0.07097 0.06929 -0.0822 0.9671 0.0155
-7.000 -0.0192 0.01109 0.00836 -0.1587 0.9353 0.0193
-6.750 0.0163 0.00955 0.00686 -0.1621 0.9303 0.0198
-6.500 0.0691 0.00793 0.00507 -0.1702 0.9254 0.0206
-6.250 0.1170 0.01344 0.00952 -0.1859 0.9292 0.0138
-6.000 0.1684 0.01200 0.00787 -0.1914 0.9204 0.0136
-5.750 0.2378 0.01061 0.00624 -0.2005 0.9011 0.0132
-5.500 0.2767 0.01071 0.00552 -0.2028 0.7261 0.0131
-5.250 0.3009 0.01073 0.00516 -0.2022 0.6522 0.0132
-5.000 0.3297 0.01059 0.00474 -0.2025 0.5963 0.0134
-4.750 0.3601 0.01044 0.00436 -0.2032 0.5542 0.0137
-4.250 0.4229 0.01016 0.00374 -0.2047 0.5008 0.0148
-4.000 0.4541 0.01005 0.00350 -0.2053 0.4826 0.0154
-3.750 0.4866 0.00987 0.00319 -0.2062 0.4672 0.0161
-3.500 0.5177 0.00978 0.00300 -0.2068 0.4532 0.0172
-3.250 0.5484 0.00972 0.00285 -0.2072 0.4412 0.0184
-3.000 0.5793 0.00965 0.00271 -0.2077 0.4303 0.0215
-2.750 0.6199 0.00901 0.00242 -0.2109 0.4191 0.1571
-2.500 0.6524 0.00884 0.00243 -0.2119 0.4107 0.2419
-2.250 0.6810 0.00893 0.00247 -0.2118 0.4019 0.2592
-2.000 0.7101 0.00897 0.00251 -0.2118 0.3951 0.2718
-1.750 0.7385 0.00907 0.00257 -0.2117 0.3874 0.2855
-1.500 0.7668 0.00916 0.00262 -0.2115 0.3811 0.2960
-1.250 0.7953 0.00924 0.00269 -0.2114 0.3744 0.3049
-1.000 0.8232 0.00938 0.00274 -0.2111 0.3676 0.3095
-0.750 0.8525 0.00940 0.00276 -0.2112 0.3628 0.3140
-0.500 0.8813 0.00948 0.00281 -0.2112 0.3575 0.3179
-0.250 0.9095 0.00960 0.00288 -0.2110 0.3514 0.3218
0.000 0.9382 0.00966 0.00292 -0.2109 0.3478 0.3256
0.250 0.9668 0.00973 0.00298 -0.2109 0.3434 0.3304
0.500 0.9953 0.00983 0.00306 -0.2108 0.3391 0.3361
0.750 1.0234 0.00997 0.00316 -0.2106 0.3346 0.3417
1.000 1.0520 0.01002 0.00323 -0.2105 0.3321 0.3476
1.250 1.0807 0.01009 0.00332 -0.2105 0.3288 0.3552
1.500 1.1088 0.01020 0.00341 -0.2103 0.3253 0.3624
1.750 1.1371 0.01032 0.00353 -0.2102 0.3217 0.3724
2.000 1.1649 0.01048 0.00368 -0.2101 0.3182 0.3825
2.250 1.1935 0.01054 0.00379 -0.2100 0.3164 0.3947
2.500 1.2219 0.01062 0.00391 -0.2099 0.3142 0.4085
2.750 1.2502 0.01072 0.00405 -0.2098 0.3116 0.4244
3.000 1.2782 0.01083 0.00419 -0.2097 0.3088 0.4418
3.250 1.3060 0.01099 0.00436 -0.2096 0.3057 0.4602
3.500 1.3335 0.01119 0.00458 -0.2093 0.3023 0.4801
3.750 1.3618 0.01126 0.00473 -0.2093 0.3009 0.5019
4.000 1.3901 0.01134 0.00488 -0.2092 0.2988 0.5262
4.250 1.4183 0.01143 0.00504 -0.2091 0.2962 0.5525
4.500 1.4462 0.01155 0.00522 -0.2090 0.2933 0.5828
4.750 1.4739 0.01172 0.00543 -0.2089 0.2896 0.6171
5.000 1.5016 0.01190 0.00570 -0.2087 0.2859 0.6624
5.250 1.5295 0.01196 0.00591 -0.2086 0.2839 0.7154
5.500 1.5566 0.01209 0.00610 -0.2083 0.2815 0.7464
5.750 1.5833 0.01224 0.00629 -0.2079 0.2789 0.7656
6.000 1.6098 0.01242 0.00649 -0.2075 0.2757 0.7797
6.250 1.6356 0.01268 0.00674 -0.2069 0.2717 0.7915
6.500 1.6624 0.01280 0.00692 -0.2066 0.2688 0.8024
6.750 1.6893 0.01290 0.00707 -0.2063 0.2653 0.8133
7.000 1.7157 0.01305 0.00724 -0.2059 0.2604 0.8247
7.250 1.7413 0.01327 0.00748 -0.2054 0.2547 0.8378
7.500 1.7678 0.01336 0.00766 -0.2050 0.2507 0.8549
7.750 1.7879 0.01336 0.00781 -0.2033 0.2464 1.0000
8.000 1.8134 0.01365 0.00808 -0.2028 0.2409 1.0000
8.250 1.8395 0.01384 0.00830 -0.2024 0.2360 1.0000
8.500 1.8648 0.01411 0.00857 -0.2018 0.2290 1.0000
8.750 1.8899 0.01440 0.00886 -0.2013 0.2223 1.0000
9.000 1.9143 0.01476 0.00919 -0.2006 0.2131 1.0000
9.250 1.9385 0.01514 0.00954 -0.1999 0.2031 1.0000
9.500 1.9615 0.01563 0.00998 -0.1991 0.1901 1.0000
9.750 1.9837 0.01622 0.01050 -0.1981 0.1757 1.0000
10.000 2.0043 0.01696 0.01114 -0.1969 0.1590 1.0000
10.250 2.0237 0.01781 0.01189 -0.1955 0.1418 1.0000
10.500 2.0420 0.01873 0.01271 -0.1940 0.1241 1.0000
10.750 2.0595 0.01967 0.01357 -0.1923 0.1092 1.0000
11.000 2.0765 0.02058 0.01442 -0.1905 0.0972 1.0000
11.250 2.0923 0.02155 0.01534 -0.1885 0.0861 1.0000
11.500 2.1067 0.02255 0.01630 -0.1863 0.0767 1.0000
11.750 2.1180 0.02362 0.01735 -0.1835 0.0682 1.0000
12.000 2.1264 0.02470 0.01842 -0.1802 0.0613 1.0000
12.250 2.1359 0.02571 0.01946 -0.1772 0.0560 1.0000
12.500 2.1427 0.02694 0.02069 -0.1738 0.0508 1.0000
12.750 2.1520 0.02801 0.02181 -0.1710 0.0476 1.0000
13.000 2.1567 0.02944 0.02326 -0.1676 0.0438 1.0000
13.250 2.1639 0.03069 0.02458 -0.1646 0.0415 1.0000
13.500 2.1681 0.03222 0.02616 -0.1615 0.0390 1.0000
13.750 2.1699 0.03398 0.02797 -0.1582 0.0369 1.0000
14.000 2.1733 0.03567 0.02974 -0.1554 0.0352 1.0000
14.250 2.1757 0.03752 0.03168 -0.1526 0.0340 1.0000
14.500 2.1751 0.03973 0.03397 -0.1499 0.0328 1.0000
14.750 2.1702 0.04245 0.03677 -0.1471 0.0314 1.0000
15.000 2.1628 0.04564 0.04006 -0.1447 0.0301 1.0000
15.250 2.1583 0.04876 0.04331 -0.1431 0.0296 1.0000
15.500 2.1507 0.05258 0.04726 -0.1420 0.0290 1.0000
15.750 2.1400 0.05737 0.05219 -0.1420 0.0284 1.0000
16.000 2.1253 0.06332 0.05830 -0.1430 0.0278 1.0000
16.250 2.1059 0.07055 0.06569 -0.1450 0.0274 1.0000
16.500 2.0817 0.07896 0.07428 -0.1476 0.0271 1.0000
16.750 2.0532 0.08822 0.08373 -0.1506 0.0269 1.0000
17.000 2.0216 0.09806 0.09375 -0.1539 0.0268 1.0000
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