S1091 (s1091-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1091 (s1091-il) Reynolds number: 50,000 Max Cl/Cd: 48.34 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1091-il-50000-n5.txt Download as CSV file: xf-s1091-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1091
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2871 0.10468 0.09808 -0.0198 1.0000 0.0627
-6.750 -0.2877 0.10292 0.09638 -0.0189 1.0000 0.0642
-6.500 -0.2866 0.10107 0.09464 -0.0188 1.0000 0.0660
-6.250 -0.2850 0.09968 0.09335 -0.0196 1.0000 0.0677
-6.000 -0.2820 0.09889 0.09267 -0.0220 1.0000 0.0688
-5.750 -0.2750 0.09817 0.09202 -0.0257 1.0000 0.0694
-5.500 -0.2666 0.09606 0.09002 -0.0282 1.0000 0.0699
-5.250 -0.2673 0.09088 0.08492 -0.0227 1.0000 0.0712
-5.000 -0.2636 0.08786 0.08197 -0.0209 1.0000 0.0730
-4.750 -0.2582 0.08543 0.07962 -0.0206 1.0000 0.0750
-4.500 -0.2511 0.08318 0.07742 -0.0213 1.0000 0.0776
-4.250 -0.2395 0.08116 0.07544 -0.0238 1.0000 0.0811
-3.750 -0.2086 0.07635 0.07069 -0.0305 1.0000 0.0855
-3.500 -0.2010 0.07332 0.06772 -0.0290 0.9989 0.0894
-3.250 -0.1432 0.07000 0.06422 -0.0428 0.9917 0.0992
-3.000 -0.1206 0.06603 0.06028 -0.0438 0.9854 0.1051
-2.500 -0.0212 0.05938 0.05335 -0.0624 0.9721 0.1259
-2.250 0.0138 0.05557 0.04951 -0.0668 0.9645 0.1295
-2.000 0.0895 0.04972 0.04316 -0.0798 0.9603 0.0684
-1.750 0.1348 0.04551 0.03872 -0.0855 0.9538 0.0533
-1.500 0.1855 0.04172 0.03467 -0.0921 0.9481 0.0485
-1.250 0.2359 0.03828 0.03087 -0.0981 0.9418 0.0477
-1.000 0.2849 0.03536 0.02755 -0.1033 0.9354 0.0501
-0.750 0.3325 0.03249 0.02413 -0.1076 0.9288 0.0501
-0.500 0.3781 0.03003 0.02106 -0.1110 0.9221 0.0505
-0.250 0.4195 0.02815 0.01854 -0.1132 0.9142 0.0539
0.000 0.4621 0.02678 0.01675 -0.1157 0.9070 0.0616
0.250 0.5006 0.02570 0.01512 -0.1170 0.8975 0.0680
0.500 0.5429 0.02473 0.01393 -0.1191 0.8898 0.0868
0.750 0.5815 0.02384 0.01316 -0.1206 0.8801 0.1539
1.000 0.6172 0.02292 0.01296 -0.1220 0.8696 0.3505
1.250 0.6521 0.02143 0.01230 -0.1227 0.8591 1.0000
1.500 0.6920 0.02136 0.01176 -0.1242 0.8487 1.0000
1.750 0.7260 0.02137 0.01150 -0.1248 0.8358 1.0000
2.000 0.7592 0.02140 0.01131 -0.1252 0.8223 1.0000
2.250 0.7923 0.02142 0.01117 -0.1255 0.8085 1.0000
2.500 0.8250 0.02144 0.01106 -0.1257 0.7940 1.0000
2.750 0.8573 0.02146 0.01099 -0.1258 0.7790 1.0000
3.000 0.8895 0.02148 0.01093 -0.1258 0.7632 1.0000
3.250 0.9170 0.02163 0.01108 -0.1251 0.7447 1.0000
3.500 0.9455 0.02174 0.01115 -0.1244 0.7256 1.0000
3.750 0.9755 0.02178 0.01114 -0.1238 0.7060 1.0000
4.000 1.0004 0.02198 0.01133 -0.1226 0.6828 1.0000
4.250 1.0266 0.02212 0.01143 -0.1214 0.6590 1.0000
4.500 1.0518 0.02228 0.01163 -0.1200 0.6329 1.0000
4.750 1.0747 0.02252 0.01184 -0.1184 0.6041 1.0000
5.000 1.0960 0.02281 0.01211 -0.1165 0.5723 1.0000
5.250 1.1168 0.02314 0.01240 -0.1146 0.5378 1.0000
5.500 1.1369 0.02352 0.01269 -0.1126 0.5008 1.0000
5.750 1.1565 0.02401 0.01310 -0.1106 0.4622 1.0000
6.000 1.1747 0.02467 0.01361 -0.1085 0.4224 1.0000
6.250 1.1921 0.02548 0.01425 -0.1065 0.3833 1.0000
6.500 1.2084 0.02642 0.01502 -0.1045 0.3454 1.0000
6.750 1.2242 0.02745 0.01594 -0.1026 0.3092 1.0000
7.250 1.2537 0.02982 0.01812 -0.0987 0.2456 1.0000
7.500 1.2681 0.03111 0.01932 -0.0968 0.2198 1.0000
7.750 1.2835 0.03245 0.02064 -0.0951 0.1983 1.0000
8.000 1.2994 0.03386 0.02204 -0.0935 0.1821 1.0000
8.250 1.3156 0.03529 0.02354 -0.0919 0.1682 1.0000
8.500 1.3319 0.03673 0.02505 -0.0904 0.1560 1.0000
8.750 1.3487 0.03822 0.02659 -0.0890 0.1460 1.0000
9.000 1.3676 0.03976 0.02823 -0.0878 0.1384 1.0000
9.250 1.3889 0.04146 0.03014 -0.0869 0.1320 1.0000
9.500 1.4098 0.04322 0.03213 -0.0860 0.1265 1.0000
9.750 1.4306 0.04509 0.03411 -0.0853 0.1215 1.0000
10.000 1.4461 0.04707 0.03648 -0.0838 0.1160 1.0000
10.250 1.4625 0.04889 0.03843 -0.0827 0.1113 1.0000
10.500 1.4795 0.05128 0.04109 -0.0816 0.1080 1.0000
10.750 1.4905 0.05403 0.04434 -0.0799 0.1051 1.0000
11.000 1.4997 0.05689 0.04766 -0.0782 0.1026 1.0000
11.250 1.5073 0.05973 0.05084 -0.0764 0.1003 1.0000
11.500 1.5179 0.06225 0.05353 -0.0750 0.0976 1.0000
11.750 1.5149 0.06537 0.05697 -0.0724 0.0955 1.0000
12.000 1.4981 0.06888 0.06092 -0.0689 0.0940 1.0000
12.250 1.4793 0.07277 0.06518 -0.0662 0.0927 1.0000
12.500 1.4581 0.07722 0.06995 -0.0644 0.0918 1.0000
12.750 1.4334 0.08248 0.07551 -0.0637 0.0912 1.0000
13.000 1.4033 0.08898 0.08226 -0.0647 0.0911 1.0000
13.250 1.3656 0.09747 0.09097 -0.0679 0.0916 1.0000
13.500 1.3196 0.10904 0.10265 -0.0743 0.0929 1.0000
13.750 1.2695 0.12416 0.11773 -0.0841 0.0943 1.0000
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Polar data table (+)
Polar graphs
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