S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il) Reynolds number: 500,000 Max Cl/Cd: 106.53 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1221-flap-il-500000-n5.txt Download as CSV file: xf-s1221-flap-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1580 0.08808 0.08566 -0.0638 0.9588 0.0112
-8.500 -0.1510 0.08320 0.08079 -0.0673 0.9557 0.0108
-8.000 -0.2552 0.03960 0.03671 -0.1062 0.9370 0.0097
-7.750 -0.1853 0.02548 0.02181 -0.1444 0.9312 0.0099
-7.500 -0.1345 0.02228 0.01832 -0.1541 0.9282 0.0102
-7.250 -0.0881 0.02020 0.01601 -0.1607 0.9247 0.0104
-7.000 -0.0485 0.01839 0.01395 -0.1650 0.9179 0.0105
-6.750 0.0020 0.01657 0.01187 -0.1711 0.9117 0.0106
-6.500 0.0513 0.01518 0.01027 -0.1764 0.9006 0.0107
-6.250 0.1278 0.01375 0.00854 -0.1873 0.8725 0.0110
-6.000 0.1775 0.01382 0.00761 -0.1921 0.6783 0.0112
-5.750 0.2055 0.01357 0.00706 -0.1925 0.6273 0.0114
-5.500 0.2350 0.01331 0.00653 -0.1931 0.5828 0.0117
-5.250 0.2659 0.01305 0.00604 -0.1940 0.5484 0.0120
-5.000 0.2974 0.01282 0.00561 -0.1949 0.5223 0.0123
-4.750 0.3307 0.01251 0.00514 -0.1963 0.5008 0.0127
-4.500 0.3635 0.01227 0.00475 -0.1975 0.4825 0.0133
-4.250 0.3954 0.01210 0.00446 -0.1983 0.4671 0.0138
-3.750 0.4582 0.01186 0.00399 -0.1997 0.4430 0.0157
-3.500 0.4898 0.01173 0.00377 -0.2005 0.4332 0.0174
-3.250 0.5210 0.01164 0.00359 -0.2010 0.4238 0.0194
-3.000 0.5527 0.01153 0.00343 -0.2017 0.4156 0.0265
-2.750 0.5868 0.01127 0.00326 -0.2032 0.4072 0.0711
-2.500 0.6238 0.01085 0.00310 -0.2055 0.3994 0.1830
-2.250 0.6546 0.01081 0.00318 -0.2061 0.3916 0.2495
-2.000 0.6831 0.01093 0.00325 -0.2060 0.3846 0.2749
-1.750 0.7120 0.01100 0.00331 -0.2059 0.3788 0.2906
-1.500 0.7408 0.01108 0.00335 -0.2059 0.3729 0.2985
-1.250 0.7694 0.01117 0.00338 -0.2058 0.3676 0.3032
-1.000 0.7982 0.01124 0.00340 -0.2058 0.3629 0.3067
-0.750 0.8268 0.01133 0.00343 -0.2057 0.3578 0.3097
-0.500 0.8554 0.01143 0.00349 -0.2056 0.3528 0.3132
-0.250 0.8841 0.01151 0.00355 -0.2056 0.3484 0.3177
0.000 0.9127 0.01160 0.00361 -0.2055 0.3439 0.3222
0.250 0.9410 0.01171 0.00369 -0.2054 0.3398 0.3263
0.500 0.9693 0.01183 0.00378 -0.2053 0.3360 0.3308
0.750 0.9978 0.01193 0.00388 -0.2052 0.3326 0.3361
1.000 1.0262 0.01203 0.00397 -0.2051 0.3289 0.3418
1.250 1.0544 0.01214 0.00408 -0.2049 0.3252 0.3476
1.500 1.0826 0.01227 0.00421 -0.2048 0.3220 0.3546
1.750 1.1104 0.01243 0.00435 -0.2046 0.3189 0.3623
2.000 1.1388 0.01254 0.00450 -0.2046 0.3165 0.3714
2.250 1.1670 0.01265 0.00464 -0.2044 0.3136 0.3809
2.500 1.1951 0.01278 0.00479 -0.2043 0.3105 0.3914
2.750 1.2229 0.01292 0.00496 -0.2041 0.3076 0.4023
3.250 1.2782 0.01328 0.00534 -0.2038 0.3025 0.4285
3.500 1.3062 0.01340 0.00553 -0.2036 0.3007 0.4435
3.750 1.3341 0.01354 0.00574 -0.2035 0.2983 0.4598
4.000 1.3619 0.01368 0.00594 -0.2033 0.2956 0.4785
4.250 1.3895 0.01384 0.00616 -0.2032 0.2930 0.4997
4.500 1.4170 0.01402 0.00641 -0.2030 0.2906 0.5230
4.750 1.4442 0.01423 0.00666 -0.2028 0.2879 0.5475
5.000 1.4716 0.01440 0.00692 -0.2026 0.2852 0.5742
5.250 1.4993 0.01454 0.00717 -0.2024 0.2824 0.6049
5.500 1.5267 0.01469 0.00744 -0.2022 0.2789 0.6409
5.750 1.5535 0.01488 0.00773 -0.2019 0.2750 0.6874
6.000 1.5793 0.01513 0.00804 -0.2014 0.2714 0.7275
6.250 1.6056 0.01532 0.00831 -0.2009 0.2687 0.7541
6.500 1.6319 0.01551 0.00857 -0.2005 0.2655 0.7715
6.750 1.6579 0.01573 0.00884 -0.2000 0.2617 0.7853
7.000 1.6835 0.01598 0.00912 -0.1995 0.2575 0.7985
7.250 1.7091 0.01620 0.00940 -0.1990 0.2531 0.8116
7.500 1.7348 0.01639 0.00968 -0.1985 0.2474 0.8264
8.000 1.7758 0.01667 0.01014 -0.1953 0.2334 1.0000
8.250 1.8001 0.01704 0.01049 -0.1946 0.2243 1.0000
8.500 1.8245 0.01740 0.01085 -0.1940 0.2154 1.0000
8.750 1.8482 0.01781 0.01126 -0.1932 0.2066 1.0000
9.000 1.8709 0.01831 0.01174 -0.1923 0.1963 1.0000
9.250 1.8927 0.01890 0.01229 -0.1913 0.1831 1.0000
9.500 1.9135 0.01958 0.01292 -0.1902 0.1683 1.0000
9.750 1.9331 0.02036 0.01364 -0.1888 0.1535 1.0000
10.000 1.9517 0.02121 0.01444 -0.1873 0.1400 1.0000
10.250 1.9690 0.02212 0.01532 -0.1856 0.1270 1.0000
10.500 1.9848 0.02311 0.01627 -0.1837 0.1148 1.0000
10.750 1.9988 0.02416 0.01729 -0.1814 0.1041 1.0000
11.000 2.0115 0.02511 0.01827 -0.1789 0.0954 1.0000
11.250 2.0222 0.02614 0.01931 -0.1761 0.0878 1.0000
11.500 2.0310 0.02731 0.02049 -0.1731 0.0803 1.0000
11.750 2.0393 0.02852 0.02172 -0.1701 0.0728 1.0000
12.000 2.0461 0.02985 0.02308 -0.1670 0.0664 1.0000
12.500 2.0565 0.03282 0.02615 -0.1608 0.0563 1.0000
12.750 2.0590 0.03457 0.02795 -0.1576 0.0523 1.0000
13.000 2.0615 0.03637 0.02984 -0.1547 0.0492 1.0000
13.250 2.0616 0.03844 0.03198 -0.1517 0.0458 1.0000
13.500 2.0588 0.04089 0.03452 -0.1488 0.0433 1.0000
13.750 2.0569 0.04338 0.03712 -0.1464 0.0411 1.0000
14.000 2.0531 0.04623 0.04009 -0.1442 0.0396 1.0000
14.250 2.0449 0.04981 0.04378 -0.1424 0.0380 1.0000
14.500 2.0316 0.05446 0.04856 -0.1415 0.0364 1.0000
14.750 2.0193 0.05967 0.05395 -0.1419 0.0357 1.0000
15.000 2.0054 0.06571 0.06018 -0.1432 0.0350 1.0000
15.250 1.9879 0.07279 0.06745 -0.1453 0.0349 1.0000
15.500 1.9658 0.08091 0.07576 -0.1479 0.0340 1.0000
15.750 1.9414 0.08948 0.08451 -0.1507 0.0336 1.0000
16.000 1.9160 0.09822 0.09342 -0.1537 0.0331 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S1221 w/ 4 deg flap (s1221-flap-il)