S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1221 w/ 4 deg flap (s1221-flap-il) Reynolds number: 500,000 Max Cl/Cd: 104.59 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1221-flap-il-500000.txt Download as CSV file: xf-s1221-flap-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2141 0.10117 0.09893 -0.0426 0.9873 0.0219
-8.500 -0.2134 0.09422 0.09199 -0.0498 0.9846 0.0228
-8.250 -0.2058 0.09006 0.08785 -0.0520 0.9817 0.0231
-8.000 -0.1869 0.08783 0.08563 -0.0537 0.9797 0.0234
-7.750 -0.1660 0.08505 0.08284 -0.0570 0.9780 0.0240
-7.500 -0.1548 0.08192 0.07973 -0.0592 0.9741 0.0246
-7.250 -0.1436 0.07767 0.07549 -0.0634 0.9701 0.0261
-7.000 -0.1671 0.06519 0.06304 -0.0755 0.9616 0.0273
-6.750 -0.1434 0.06476 0.06264 -0.0751 0.9585 0.0279
-6.500 -0.1122 0.06239 0.06026 -0.0796 0.9560 0.0285
-6.250 -0.1012 0.05882 0.05671 -0.0827 0.9487 0.0292
-6.000 -0.0072 0.03016 0.02717 -0.1474 0.9438 0.0340
-5.750 0.0575 0.02731 0.02387 -0.1586 0.9420 0.0381
-5.500 0.1412 0.01704 0.01243 -0.1745 0.9416 0.0218
-5.250 0.1792 0.01474 0.00978 -0.1768 0.9341 0.0197
-5.000 0.2254 0.01339 0.00828 -0.1803 0.9279 0.0193
-4.750 0.2664 0.01231 0.00715 -0.1829 0.9157 0.0195
-4.500 0.3351 0.01101 0.00577 -0.1914 0.8926 0.0202
-4.250 0.4087 0.01115 0.00484 -0.2008 0.6817 0.0216
-4.000 0.4354 0.01124 0.00459 -0.2005 0.6194 0.0224
-3.750 0.4657 0.01115 0.00420 -0.2011 0.5723 0.0237
-3.500 0.4954 0.01114 0.00398 -0.2015 0.5390 0.0261
-3.250 0.5270 0.01105 0.00371 -0.2023 0.5141 0.0301
-3.000 0.5727 0.01012 0.00325 -0.2070 0.4928 0.2171
-2.750 0.6013 0.01025 0.00332 -0.2069 0.4773 0.2615
-2.500 0.6294 0.01040 0.00338 -0.2067 0.4638 0.2793
-2.250 0.6572 0.01060 0.00349 -0.2065 0.4518 0.2972
-2.000 0.6850 0.01079 0.00361 -0.2062 0.4410 0.3139
-1.750 0.7128 0.01099 0.00374 -0.2059 0.4318 0.3258
-1.500 0.7414 0.01108 0.00377 -0.2059 0.4230 0.3331
-1.250 0.7699 0.01118 0.00381 -0.2057 0.4153 0.3381
-1.000 0.7984 0.01129 0.00384 -0.2056 0.4078 0.3427
-0.750 0.8269 0.01141 0.00387 -0.2055 0.4009 0.3466
-0.500 0.8560 0.01144 0.00391 -0.2056 0.3944 0.3509
-0.250 0.8844 0.01157 0.00398 -0.2055 0.3881 0.3555
0.000 0.9127 0.01171 0.00406 -0.2054 0.3828 0.3608
0.250 0.9418 0.01177 0.00413 -0.2054 0.3778 0.3665
0.500 0.9702 0.01189 0.00422 -0.2053 0.3728 0.3726
0.750 0.9981 0.01210 0.00435 -0.2052 0.3678 0.3791
1.000 1.0273 0.01214 0.00445 -0.2052 0.3638 0.3866
1.250 1.0557 0.01226 0.00457 -0.2051 0.3597 0.3954
1.500 1.0843 0.01239 0.00471 -0.2051 0.3559 0.4049
1.750 1.1122 0.01263 0.00490 -0.2050 0.3519 0.4162
2.000 1.1409 0.01273 0.00506 -0.2050 0.3489 0.4297
2.250 1.1696 0.01282 0.00521 -0.2050 0.3454 0.4451
2.500 1.1980 0.01295 0.00538 -0.2049 0.3421 0.4623
2.750 1.2262 0.01312 0.00558 -0.2048 0.3390 0.4817
3.000 1.2544 0.01338 0.00584 -0.2048 0.3356 0.5037
3.250 1.2830 0.01352 0.00608 -0.2048 0.3332 0.5292
3.500 1.3115 0.01363 0.00629 -0.2048 0.3305 0.5576
3.750 1.3398 0.01375 0.00652 -0.2047 0.3275 0.5903
4.000 1.3680 0.01390 0.00676 -0.2046 0.3246 0.6293
4.250 1.3956 0.01410 0.00706 -0.2045 0.3219 0.6780
4.500 1.4223 0.01447 0.00747 -0.2041 0.3185 0.7249
4.750 1.4490 0.01459 0.00769 -0.2036 0.3162 0.7572
5.000 1.4756 0.01474 0.00792 -0.2032 0.3133 0.7804
5.250 1.5022 0.01491 0.00814 -0.2028 0.3101 0.8000
5.500 1.5284 0.01508 0.00834 -0.2023 0.3067 0.8179
5.750 1.5542 0.01542 0.00867 -0.2018 0.3027 0.8370
6.000 1.5793 0.01548 0.00889 -0.2011 0.3001 0.8641
6.250 1.5970 0.01543 0.00900 -0.1987 0.2974 1.0000
6.500 1.6238 0.01564 0.00923 -0.1984 0.2942 1.0000
6.750 1.6501 0.01589 0.00949 -0.1980 0.2908 1.0000
7.000 1.6760 0.01633 0.00987 -0.1977 0.2867 1.0000
7.250 1.7021 0.01644 0.01009 -0.1972 0.2833 1.0000
7.500 1.7278 0.01660 0.01031 -0.1967 0.2790 1.0000
7.750 1.7529 0.01682 0.01053 -0.1961 0.2741 1.0000
8.000 1.7777 0.01712 0.01084 -0.1955 0.2690 1.0000
8.250 1.8032 0.01724 0.01106 -0.1950 0.2637 1.0000
8.500 1.8277 0.01750 0.01133 -0.1943 0.2587 1.0000
8.750 1.8518 0.01782 0.01168 -0.1936 0.2538 1.0000
9.000 1.8768 0.01802 0.01198 -0.1930 0.2483 1.0000
9.250 1.9001 0.01834 0.01230 -0.1921 0.2418 1.0000
9.500 1.9243 0.01861 0.01265 -0.1914 0.2350 1.0000
9.750 1.9468 0.01899 0.01303 -0.1904 0.2269 1.0000
10.000 1.9698 0.01935 0.01345 -0.1896 0.2181 1.0000
10.250 1.9911 0.01985 0.01394 -0.1884 0.2070 1.0000
10.500 2.0109 0.02047 0.01453 -0.1871 0.1939 1.0000
10.750 2.0291 0.02122 0.01526 -0.1855 0.1789 1.0000
11.000 2.0450 0.02215 0.01613 -0.1836 0.1626 1.0000
11.250 2.0573 0.02328 0.01720 -0.1810 0.1464 1.0000
11.500 2.0669 0.02447 0.01834 -0.1781 0.1325 1.0000
11.750 2.0739 0.02580 0.01962 -0.1748 0.1187 1.0000
12.000 2.0801 0.02719 0.02099 -0.1714 0.1067 1.0000
12.250 2.0855 0.02864 0.02245 -0.1681 0.0961 1.0000
12.500 2.0894 0.03021 0.02404 -0.1646 0.0872 1.0000
12.750 2.0905 0.03203 0.02587 -0.1610 0.0791 1.0000
13.000 2.0903 0.03398 0.02785 -0.1575 0.0720 1.0000
13.250 2.0899 0.03602 0.02995 -0.1542 0.0663 1.0000
13.500 2.0857 0.03847 0.03246 -0.1508 0.0619 1.0000
13.750 2.0818 0.04103 0.03511 -0.1478 0.0581 1.0000
14.000 2.0769 0.04384 0.03803 -0.1452 0.0555 1.0000
14.250 2.0657 0.04752 0.04182 -0.1429 0.0530 1.0000
14.500 2.0496 0.05221 0.04664 -0.1413 0.0509 1.0000
14.750 2.0395 0.05680 0.05140 -0.1410 0.0497 1.0000
15.000 2.0256 0.06255 0.05733 -0.1419 0.0485 1.0000
15.250 2.0058 0.06980 0.06477 -0.1439 0.0478 1.0000
15.500 1.9825 0.07805 0.07320 -0.1465 0.0468 1.0000
15.750 1.9560 0.08694 0.08227 -0.1494 0.0462 1.0000
16.000 1.9286 0.09601 0.09150 -0.1524 0.0455 1.0000
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