S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1223 RTL (s1223rtl-il) Reynolds number: 50,000 Max Cl/Cd: 35.91 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1223rtl-il-50000-n5.txt Download as CSV file: xf-s1223rtl-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1223 RTL
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
------ -------- --------- --------- -------- -------- --------
-5.750 -0.0207 0.10861 0.10306 -0.0509 0.9100 0.1089
-5.500 -0.0230 0.10773 0.10226 -0.0525 0.8952 0.1122
-5.250 -0.0300 0.10744 0.10205 -0.0558 0.8791 0.1134
-5.000 -0.0007 0.10124 0.09588 -0.0552 0.8688 0.1154
-4.750 0.0187 0.09739 0.09205 -0.0554 0.8538 0.1186
-4.500 0.0279 0.09475 0.08946 -0.0557 0.8354 0.1223
-4.250 0.0246 0.09378 0.08857 -0.0586 0.8103 0.1280
-4.000 0.0342 0.09060 0.08547 -0.0608 0.7859 0.1298
-3.500 0.0561 0.08456 0.07949 -0.0560 0.7193 0.1386
-3.000 0.1330 0.06985 0.06427 -0.0792 0.6468 0.0739
-2.750 0.2049 0.06123 0.05506 -0.0957 0.6038 0.0646
-2.500 0.2649 0.05558 0.04880 -0.1076 0.5661 0.0621
-2.250 0.3721 0.04594 0.03829 -0.1357 0.5363 0.0623
-2.000 0.5723 0.03436 0.02429 -0.1833 0.5050 0.0657
-1.750 0.6228 0.03322 0.02273 -0.1888 0.4911 0.0713
-1.500 0.6830 0.03189 0.02062 -0.1957 0.4794 0.0766
-1.250 0.7318 0.03125 0.01960 -0.2000 0.4692 0.0858
-1.000 0.7860 0.03078 0.01875 -0.2053 0.4610 0.0990
-0.750 0.8387 0.03041 0.01834 -0.2105 0.4527 0.1230
-0.500 0.8964 0.03019 0.01832 -0.2168 0.4447 0.2107
-0.250 0.9382 0.03086 0.01901 -0.2191 0.4386 0.3260
0.000 0.9671 0.03161 0.01984 -0.2187 0.4327 0.3871
0.250 0.9994 0.03216 0.02028 -0.2190 0.4275 0.4273
0.500 1.0394 0.03257 0.02035 -0.2213 0.4228 0.4547
0.750 1.0769 0.03299 0.02051 -0.2230 0.4185 0.4759
1.000 1.1084 0.03339 0.02083 -0.2237 0.4137 0.4947
1.250 1.1404 0.03382 0.02115 -0.2246 0.4090 0.5137
1.500 1.1732 0.03429 0.02146 -0.2255 0.4048 0.5333
1.750 1.2071 0.03480 0.02178 -0.2266 0.4012 0.5542
2.000 1.2380 0.03537 0.02227 -0.2273 0.3980 0.5754
2.250 1.2648 0.03597 0.02292 -0.2272 0.3944 0.5976
2.500 1.2924 0.03659 0.02356 -0.2273 0.3907 0.6216
2.750 1.3190 0.03717 0.02416 -0.2272 0.3873 0.6470
3.000 1.3467 0.03776 0.02472 -0.2272 0.3840 0.6767
3.250 1.3746 0.03833 0.02525 -0.2273 0.3812 0.7120
3.500 1.3972 0.03891 0.02594 -0.2263 0.3785 0.7561
3.750 1.4066 0.03930 0.02666 -0.2228 0.3758 0.8554
4.250 1.4587 0.04149 0.02881 -0.2233 0.3697 1.0000
4.500 1.4846 0.04257 0.02985 -0.2234 0.3667 1.0000
4.750 1.5110 0.04361 0.03078 -0.2235 0.3640 1.0000
5.000 1.5386 0.04463 0.03166 -0.2237 0.3615 1.0000
5.250 1.5618 0.04586 0.03285 -0.2233 0.3591 1.0000
5.500 1.5739 0.04744 0.03467 -0.2212 0.3564 1.0000
5.750 1.5870 0.04906 0.03645 -0.2193 0.3538 1.0000
6.000 1.6007 0.05067 0.03819 -0.2175 0.3513 1.0000
6.250 1.6149 0.05224 0.03985 -0.2158 0.3487 1.0000
6.500 1.6307 0.05371 0.04138 -0.2144 0.3463 1.0000
6.750 1.6494 0.05506 0.04278 -0.2133 0.3441 1.0000
7.000 1.6719 0.05631 0.04399 -0.2128 0.3420 1.0000
7.250 1.6835 0.05815 0.04592 -0.2109 0.3400 1.0000
7.500 1.6649 0.06143 0.04960 -0.2052 0.3375 1.0000
7.750 1.6391 0.06510 0.05363 -0.1989 0.3352 1.0000
8.000 1.6025 0.06959 0.05846 -0.1920 0.3327 1.0000
8.250 1.5566 0.07546 0.06468 -0.1857 0.3298 1.0000
8.500 1.5188 0.08167 0.07114 -0.1817 0.3269 1.0000
8.750 1.5195 0.08482 0.07434 -0.1803 0.3246 1.0000
9.000 1.5355 0.08658 0.07610 -0.1796 0.3229 1.0000
9.500 1.2940 0.13106 0.12153 -0.1899 0.3054 1.0000
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Polar data table (+)
Polar graphs
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