S8055 (12%) (s8055-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S8055 (12%) (s8055-il) Reynolds number: 50,000 Max Cl/Cd: 32.17 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8055-il-50000.txt Download as CSV file: xf-s8055-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S8055 (12%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3892 0.11034 0.10355 -0.0241 1.0000 0.2758
-9.250 -0.3703 0.10558 0.09879 -0.0234 1.0000 0.2833
-9.000 -0.3837 0.10369 0.09703 -0.0239 1.0000 0.2939
-8.750 -0.3833 0.10115 0.09456 -0.0232 1.0000 0.3074
-8.500 -0.3644 0.09688 0.09030 -0.0220 1.0000 0.3190
-8.250 -0.3630 0.09394 0.08745 -0.0211 1.0000 0.3303
-7.000 -0.5571 0.07160 0.06564 -0.0292 1.0000 0.1632
-6.750 -0.5933 0.06475 0.05825 -0.0296 1.0000 0.1365
-6.500 -0.6021 0.05931 0.05244 -0.0282 1.0000 0.1243
-6.250 -0.5953 0.05572 0.04868 -0.0265 1.0000 0.1189
-6.000 -0.5935 0.05138 0.04392 -0.0248 1.0000 0.1129
-5.750 -0.5884 0.04739 0.03909 -0.0228 1.0000 0.1073
-5.500 -0.5761 0.04416 0.03553 -0.0212 1.0000 0.1061
-5.250 -0.5620 0.04133 0.03223 -0.0195 1.0000 0.1065
-5.000 -0.5455 0.03887 0.02918 -0.0179 1.0000 0.1081
-4.750 -0.5270 0.03630 0.02655 -0.0168 1.0000 0.1122
-4.500 -0.5061 0.03425 0.02421 -0.0155 1.0000 0.1162
-4.250 -0.4843 0.03242 0.02189 -0.0141 1.0000 0.1239
-4.000 -0.4624 0.03076 0.02018 -0.0129 1.0000 0.1354
-3.750 -0.4400 0.02910 0.01852 -0.0116 1.0000 0.1547
-3.500 -0.4183 0.02756 0.01719 -0.0102 1.0000 0.1872
-3.250 -0.3966 0.02575 0.01584 -0.0088 1.0000 0.2575
-3.000 -0.3871 0.02266 0.01479 -0.0050 1.0000 0.4978
-2.750 -0.3920 0.02243 0.01590 0.0063 1.0000 0.7827
-2.500 -0.1363 0.02610 0.01796 -0.0260 1.0000 1.0000
-2.250 -0.1434 0.02561 0.01734 -0.0226 1.0000 1.0000
-2.000 -0.1487 0.02521 0.01679 -0.0191 1.0000 1.0000
-1.750 -0.1525 0.02487 0.01632 -0.0157 1.0000 1.0000
-1.500 -0.1549 0.02459 0.01589 -0.0124 1.0000 1.0000
-1.250 -0.1551 0.02438 0.01554 -0.0093 1.0000 1.0000
-1.000 -0.1521 0.02427 0.01526 -0.0066 1.0000 1.0000
-0.750 -0.1462 0.02427 0.01508 -0.0043 1.0000 1.0000
-0.500 -0.1372 0.02438 0.01500 -0.0025 1.0000 1.0000
-0.250 -0.1258 0.02460 0.01504 -0.0011 1.0000 1.0000
0.000 -0.1126 0.02491 0.01518 0.0001 1.0000 1.0000
0.250 -0.0984 0.02529 0.01540 0.0010 1.0000 1.0000
0.500 -0.0835 0.02573 0.01570 0.0017 1.0000 1.0000
0.750 -0.0681 0.02624 0.01608 0.0023 1.0000 1.0000
1.000 -0.0524 0.02681 0.01654 0.0029 1.0000 1.0000
1.250 -0.0151 0.02807 0.01767 -0.0008 0.9908 1.0000
1.500 0.0350 0.02972 0.01921 -0.0068 0.9743 1.0000
1.750 0.0833 0.03127 0.02067 -0.0121 0.9571 1.0000
2.000 0.1221 0.03243 0.02179 -0.0156 0.9389 1.0000
2.250 0.1622 0.03362 0.02294 -0.0190 0.9201 1.0000
2.500 0.2058 0.03482 0.02412 -0.0228 0.9006 1.0000
2.750 0.2488 0.03593 0.02523 -0.0262 0.8810 1.0000
3.000 0.2800 0.03673 0.02605 -0.0275 0.8598 1.0000
3.250 0.3217 0.03755 0.02692 -0.0302 0.8388 1.0000
3.500 0.3655 0.03823 0.02766 -0.0328 0.8181 1.0000
3.750 0.3943 0.03876 0.02825 -0.0331 0.7952 1.0000
4.000 0.4436 0.03892 0.02853 -0.0357 0.7740 1.0000
4.250 0.4734 0.03917 0.02887 -0.0356 0.7508 1.0000
4.500 0.5206 0.03878 0.02862 -0.0371 0.7289 1.0000
4.750 0.5585 0.03836 0.02833 -0.0372 0.7056 1.0000
5.000 0.6141 0.03688 0.02706 -0.0385 0.6837 1.0000
5.250 0.6602 0.03536 0.02572 -0.0382 0.6611 1.0000
5.500 0.7151 0.03301 0.02358 -0.0382 0.6385 1.0000
5.750 0.7611 0.03110 0.02181 -0.0374 0.6116 1.0000
6.000 0.8096 0.02915 0.01994 -0.0368 0.5803 1.0000
6.250 0.8533 0.02782 0.01852 -0.0360 0.5442 1.0000
6.500 0.8800 0.02784 0.01842 -0.0342 0.5070 1.0000
6.750 0.9049 0.02820 0.01863 -0.0325 0.4713 1.0000
7.000 0.9284 0.02886 0.01912 -0.0309 0.4388 1.0000
7.250 0.9495 0.02975 0.01990 -0.0293 0.4092 1.0000
7.500 0.9706 0.03080 0.02086 -0.0279 0.3826 1.0000
7.750 0.9948 0.03187 0.02176 -0.0268 0.3578 1.0000
8.000 1.0107 0.03329 0.02326 -0.0251 0.3358 1.0000
8.250 1.0308 0.03468 0.02462 -0.0238 0.3150 1.0000
8.500 1.0542 0.03612 0.02593 -0.0229 0.2952 1.0000
8.750 1.0690 0.03787 0.02783 -0.0212 0.2779 1.0000
9.000 1.0844 0.03968 0.02974 -0.0196 0.2618 1.0000
9.250 1.1009 0.04162 0.03176 -0.0182 0.2473 1.0000
9.500 1.1184 0.04357 0.03377 -0.0169 0.2335 1.0000
9.750 1.1263 0.04583 0.03632 -0.0147 0.2225 1.0000
10.000 1.1298 0.04869 0.03949 -0.0123 0.2143 1.0000
10.250 1.1499 0.05086 0.04162 -0.0115 0.2036 1.0000
10.500 1.1352 0.05429 0.04557 -0.0078 0.1990 1.0000
10.750 1.1418 0.05710 0.04855 -0.0061 0.1926 1.0000
11.000 1.1419 0.06062 0.05224 -0.0041 0.1882 1.0000
11.250 1.1142 0.06487 0.05683 -0.0006 0.1871 1.0000
11.500 1.0799 0.06936 0.06152 0.0028 0.1871 1.0000
11.750 1.0429 0.07491 0.06722 0.0045 0.1880 1.0000
12.000 1.0051 0.08175 0.07415 0.0042 0.1892 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S8055 (12%) (s8055-il)