S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.46 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1221-flap-il-1000000-n5.txt Download as CSV file: xf-s1221-flap-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1910 0.10068 0.09886 -0.0614 0.9655 0.0071
-10.000 -0.1857 0.09728 0.09546 -0.0627 0.9593 0.0070
-9.250 -0.3235 0.04158 0.03923 -0.1076 0.9417 0.0073
-8.750 -0.2213 0.02048 0.01717 -0.1623 0.9275 0.0074
-8.500 -0.1686 0.01763 0.01403 -0.1722 0.9230 0.0075
-8.250 -0.1185 0.01586 0.01205 -0.1792 0.9163 0.0076
-8.000 -0.0606 0.01458 0.01059 -0.1872 0.9067 0.0077
-7.750 -0.0053 0.01369 0.00952 -0.1940 0.8871 0.0079
-7.500 0.0171 0.01394 0.00897 -0.1932 0.7098 0.0080
-7.250 0.0436 0.01365 0.00837 -0.1936 0.6548 0.0081
-7.000 0.0730 0.01325 0.00769 -0.1944 0.6072 0.0082
-6.750 0.1036 0.01287 0.00707 -0.1954 0.5661 0.0083
-6.500 0.1350 0.01251 0.00651 -0.1965 0.5345 0.0084
-6.250 0.1671 0.01217 0.00600 -0.1977 0.5098 0.0085
-6.000 0.1994 0.01185 0.00553 -0.1988 0.4900 0.0087
-5.750 0.2317 0.01157 0.00511 -0.1999 0.4727 0.0089
-5.500 0.2640 0.01132 0.00474 -0.2009 0.4575 0.0091
-5.250 0.2960 0.01110 0.00441 -0.2018 0.4447 0.0093
-5.000 0.3277 0.01092 0.00413 -0.2026 0.4340 0.0096
-4.750 0.3590 0.01077 0.00390 -0.2033 0.4241 0.0097
-4.500 0.3919 0.01052 0.00356 -0.2043 0.4154 0.0102
-4.250 0.4233 0.01038 0.00334 -0.2050 0.4068 0.0106
-4.000 0.4541 0.01028 0.00318 -0.2055 0.3994 0.0110
-3.750 0.4847 0.01020 0.00303 -0.2059 0.3921 0.0115
-3.500 0.5150 0.01015 0.00291 -0.2063 0.3846 0.0120
-3.250 0.5454 0.01009 0.00280 -0.2066 0.3781 0.0128
-3.000 0.5757 0.01005 0.00271 -0.2070 0.3706 0.0146
-2.750 0.6063 0.00999 0.00262 -0.2074 0.3651 0.0197
-2.500 0.6385 0.00983 0.00253 -0.2082 0.3596 0.0514
-2.250 0.6729 0.00956 0.00242 -0.2097 0.3537 0.1260
-2.000 0.7069 0.00931 0.00240 -0.2112 0.3491 0.2203
-1.750 0.7366 0.00932 0.00245 -0.2114 0.3446 0.2512
-1.500 0.7656 0.00937 0.00250 -0.2114 0.3396 0.2678
-1.250 0.7941 0.00946 0.00255 -0.2113 0.3346 0.2781
-1.000 0.8230 0.00950 0.00259 -0.2112 0.3307 0.2846
-0.750 0.8517 0.00957 0.00262 -0.2112 0.3268 0.2874
-0.500 0.8802 0.00966 0.00267 -0.2110 0.3229 0.2900
0.000 0.9372 0.00982 0.00277 -0.2108 0.3159 0.2964
0.250 0.9658 0.00989 0.00284 -0.2107 0.3126 0.3007
0.500 0.9942 0.00997 0.00291 -0.2106 0.3094 0.3046
0.750 1.0224 0.01008 0.00298 -0.2105 0.3063 0.3082
1.000 1.0506 0.01018 0.00307 -0.2103 0.3032 0.3122
1.250 1.0790 0.01026 0.00316 -0.2102 0.3010 0.3175
1.500 1.1073 0.01034 0.00325 -0.2101 0.2987 0.3228
2.000 1.1636 0.01053 0.00346 -0.2098 0.2937 0.3345
2.250 1.1915 0.01065 0.00357 -0.2096 0.2913 0.3414
2.500 1.2195 0.01077 0.00370 -0.2094 0.2889 0.3489
2.750 1.2473 0.01090 0.00384 -0.2092 0.2864 0.3585
3.000 1.2754 0.01098 0.00396 -0.2091 0.2849 0.3679
3.250 1.3033 0.01108 0.00409 -0.2089 0.2830 0.3779
3.500 1.3313 0.01118 0.00424 -0.2088 0.2809 0.3890
3.750 1.3590 0.01130 0.00438 -0.2086 0.2788 0.4006
4.000 1.3867 0.01143 0.00454 -0.2084 0.2764 0.4137
4.250 1.4142 0.01158 0.00471 -0.2082 0.2732 0.4282
4.500 1.4416 0.01173 0.00490 -0.2080 0.2702 0.4434
4.750 1.4694 0.01183 0.00505 -0.2078 0.2677 0.4597
5.000 1.4970 0.01195 0.00522 -0.2077 0.2641 0.4786
5.250 1.5244 0.01209 0.00541 -0.2075 0.2604 0.5005
5.500 1.5517 0.01226 0.00562 -0.2073 0.2571 0.5236
5.750 1.5790 0.01241 0.00583 -0.2070 0.2544 0.5471
6.000 1.6065 0.01253 0.00603 -0.2069 0.2513 0.5727
6.250 1.6338 0.01268 0.00625 -0.2067 0.2474 0.6023
6.500 1.6608 0.01289 0.00650 -0.2064 0.2414 0.6363
6.750 1.6881 0.01304 0.00676 -0.2063 0.2360 0.6857
7.000 1.7141 0.01331 0.00705 -0.2059 0.2270 0.7268
7.250 1.7396 0.01359 0.00733 -0.2053 0.2168 0.7496
7.500 1.7646 0.01393 0.00764 -0.2048 0.2068 0.7627
7.750 1.7893 0.01430 0.00798 -0.2041 0.1970 0.7736
8.000 1.8138 0.01467 0.00833 -0.2035 0.1869 0.7838
8.250 1.8374 0.01517 0.00877 -0.2027 0.1727 0.7936
8.500 1.8601 0.01576 0.00929 -0.2018 0.1574 0.8027
8.750 1.8827 0.01636 0.00984 -0.2008 0.1435 0.8115
9.000 1.9049 0.01696 0.01040 -0.1999 0.1309 0.8201
9.250 1.9266 0.01760 0.01101 -0.1988 0.1185 0.8300
9.500 1.9478 0.01828 0.01167 -0.1977 0.1064 0.8455
9.750 1.9637 0.01870 0.01220 -0.1954 0.0980 1.0000
10.000 1.9841 0.01939 0.01285 -0.1941 0.0892 1.0000
10.250 2.0033 0.02016 0.01358 -0.1926 0.0798 1.0000
10.500 2.0207 0.02106 0.01442 -0.1909 0.0690 1.0000
10.750 2.0372 0.02198 0.01530 -0.1891 0.0600 1.0000
11.000 2.0534 0.02284 0.01616 -0.1871 0.0535 1.0000
11.250 2.0683 0.02373 0.01705 -0.1849 0.0482 1.0000
11.500 2.0801 0.02466 0.01799 -0.1822 0.0442 1.0000
11.750 2.0913 0.02551 0.01888 -0.1794 0.0411 1.0000
12.000 2.1015 0.02648 0.01988 -0.1765 0.0380 1.0000
12.250 2.1107 0.02753 0.02096 -0.1735 0.0354 1.0000
12.500 2.1210 0.02853 0.02201 -0.1708 0.0337 1.0000
12.750 2.1292 0.02970 0.02323 -0.1679 0.0319 1.0000
13.000 2.1350 0.03107 0.02465 -0.1648 0.0299 1.0000
13.250 2.1425 0.03233 0.02599 -0.1620 0.0288 1.0000
13.500 2.1476 0.03382 0.02755 -0.1592 0.0274 1.0000
13.750 2.1511 0.03549 0.02929 -0.1563 0.0264 1.0000
14.000 2.1510 0.03755 0.03141 -0.1533 0.0248 1.0000
14.250 2.1536 0.03946 0.03341 -0.1508 0.0242 1.0000
14.500 2.1541 0.04166 0.03571 -0.1484 0.0235 1.0000
14.750 2.1511 0.04432 0.03847 -0.1461 0.0225 1.0000
15.000 2.1449 0.04753 0.04177 -0.1441 0.0217 1.0000
15.250 2.1364 0.05132 0.04568 -0.1427 0.0211 1.0000
15.500 2.1238 0.05619 0.05069 -0.1424 0.0204 1.0000
15.750 2.1116 0.06167 0.05632 -0.1432 0.0200 1.0000
16.000 2.0956 0.06824 0.06305 -0.1448 0.0195 1.0000
16.250 2.0756 0.07583 0.07082 -0.1471 0.0193 1.0000
16.500 2.0507 0.08448 0.07965 -0.1499 0.0191 1.0000
16.750 2.0229 0.09364 0.08898 -0.1529 0.0190 1.0000
17.000 1.9941 0.10299 0.09850 -0.1561 0.0188 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S1221 w/ 4 deg flap (s1221-flap-il)