S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8052 (11.88%) (s8052-il) Reynolds number: 50,000 Max Cl/Cd: 30.98 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8052-il-50000.txt Download as CSV file: xf-s8052-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S8052 (11.88%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4216 0.09994 0.09326 -0.0090 1.0000 0.3195
-8.500 -0.4101 0.09591 0.08925 -0.0093 1.0000 0.3243
-8.250 -0.5440 0.07591 0.06950 -0.0390 1.0000 0.1514
-8.000 -0.5543 0.06930 0.06282 -0.0407 1.0000 0.1350
-7.750 -0.5828 0.06333 0.05654 -0.0412 1.0000 0.1220
-7.500 -0.5803 0.05964 0.05284 -0.0398 1.0000 0.1193
-7.250 -0.5869 0.05609 0.04914 -0.0377 1.0000 0.1167
-7.000 -0.5973 0.05254 0.04526 -0.0348 1.0000 0.1134
-6.750 -0.6103 0.04949 0.04139 -0.0310 1.0000 0.1087
-6.500 -0.6072 0.04668 0.03827 -0.0284 1.0000 0.1085
-6.250 -0.6004 0.04393 0.03523 -0.0260 1.0000 0.1082
-6.000 -0.5911 0.04123 0.03219 -0.0237 1.0000 0.1080
-5.750 -0.5790 0.03867 0.02924 -0.0217 1.0000 0.1081
-5.500 -0.5643 0.03636 0.02646 -0.0197 1.0000 0.1090
-5.250 -0.5469 0.03392 0.02397 -0.0183 1.0000 0.1122
-5.000 -0.5289 0.03225 0.02215 -0.0167 1.0000 0.1189
-4.750 -0.5097 0.03048 0.02021 -0.0152 1.0000 0.1280
-4.500 -0.4888 0.02884 0.01849 -0.0137 1.0000 0.1412
-4.250 -0.4685 0.02737 0.01706 -0.0122 1.0000 0.1656
-4.000 -0.4500 0.02564 0.01571 -0.0104 1.0000 0.2133
-3.750 -0.4363 0.02298 0.01421 -0.0081 1.0000 0.3472
-3.500 -0.4383 0.02141 0.01460 -0.0005 1.0000 0.5993
-3.250 -0.4386 0.02203 0.01546 0.0081 1.0000 0.7274
-3.000 -0.4363 0.02266 0.01609 0.0163 1.0000 0.8031
-2.750 -0.4151 0.02358 0.01684 0.0220 1.0000 0.8756
-2.500 -0.1347 0.02617 0.01783 -0.0167 1.0000 0.9844
-2.250 -0.0838 0.02560 0.01694 -0.0238 1.0000 1.0000
-2.000 -0.0917 0.02534 0.01661 -0.0206 1.0000 1.0000
-1.750 -0.0991 0.02508 0.01626 -0.0173 1.0000 1.0000
-1.500 -0.1061 0.02481 0.01592 -0.0139 1.0000 1.0000
-1.250 -0.1131 0.02453 0.01556 -0.0104 1.0000 1.0000
-1.000 -0.1201 0.02422 0.01519 -0.0069 1.0000 1.0000
-0.750 -0.1261 0.02393 0.01480 -0.0033 1.0000 1.0000
-0.500 -0.1288 0.02371 0.01448 -0.0003 1.0000 1.0000
-0.250 -0.1262 0.02365 0.01428 0.0021 1.0000 1.0000
0.000 -0.1177 0.02377 0.01425 0.0035 1.0000 1.0000
0.250 -0.1055 0.02404 0.01437 0.0044 1.0000 1.0000
0.500 -0.0882 0.02447 0.01466 0.0044 0.9988 1.0000
0.750 -0.0395 0.02574 0.01578 -0.0014 0.9853 1.0000
1.000 0.0064 0.02695 0.01687 -0.0064 0.9716 1.0000
1.250 0.0511 0.02811 0.01793 -0.0111 0.9569 1.0000
1.500 0.0948 0.02923 0.01899 -0.0155 0.9416 1.0000
1.750 0.1340 0.03021 0.01992 -0.0188 0.9250 1.0000
2.000 0.1702 0.03113 0.02081 -0.0215 0.9075 1.0000
2.250 0.2078 0.03204 0.02172 -0.0241 0.8889 1.0000
2.500 0.2501 0.03294 0.02263 -0.0273 0.8698 1.0000
2.750 0.2974 0.03378 0.02351 -0.0309 0.8505 1.0000
3.000 0.3256 0.03445 0.02423 -0.0314 0.8290 1.0000
3.250 0.3729 0.03497 0.02483 -0.0343 0.8079 1.0000
3.500 0.4091 0.03543 0.02536 -0.0354 0.7857 1.0000
3.750 0.4562 0.03551 0.02558 -0.0374 0.7631 1.0000
4.000 0.4999 0.03543 0.02563 -0.0386 0.7403 1.0000
4.250 0.5439 0.03494 0.02531 -0.0391 0.7175 1.0000
4.500 0.5826 0.03432 0.02482 -0.0385 0.6943 1.0000
4.750 0.6257 0.03314 0.02377 -0.0377 0.6713 1.0000
5.000 0.6574 0.03231 0.02308 -0.0358 0.6457 1.0000
5.250 0.6990 0.03068 0.02156 -0.0342 0.6211 1.0000
5.500 0.7384 0.02902 0.01996 -0.0323 0.5940 1.0000
5.750 0.7672 0.02812 0.01908 -0.0299 0.5618 1.0000
6.000 0.7957 0.02750 0.01839 -0.0277 0.5274 1.0000
6.250 0.8245 0.02715 0.01788 -0.0257 0.4925 1.0000
6.500 0.8497 0.02743 0.01797 -0.0239 0.4585 1.0000
6.750 0.8709 0.02815 0.01856 -0.0222 0.4262 1.0000
7.000 0.8933 0.02903 0.01928 -0.0207 0.3972 1.0000
7.250 0.9165 0.02998 0.02008 -0.0195 0.3705 1.0000
7.500 0.9343 0.03131 0.02147 -0.0179 0.3461 1.0000
7.750 0.9576 0.03257 0.02258 -0.0169 0.3239 1.0000
8.000 0.9746 0.03412 0.02425 -0.0155 0.3032 1.0000
8.250 0.9952 0.03562 0.02574 -0.0144 0.2838 1.0000
8.500 1.0180 0.03724 0.02725 -0.0135 0.2659 1.0000
8.750 1.0339 0.03913 0.02928 -0.0121 0.2498 1.0000
9.000 1.0517 0.04117 0.03139 -0.0109 0.2355 1.0000
9.250 1.0675 0.04318 0.03352 -0.0096 0.2220 1.0000
9.500 1.0703 0.04607 0.03689 -0.0074 0.2127 1.0000
9.750 1.0826 0.04877 0.03976 -0.0060 0.2037 1.0000
10.000 1.0965 0.05109 0.04219 -0.0048 0.1940 1.0000
10.250 1.0901 0.05470 0.04620 -0.0025 0.1889 1.0000
10.500 1.0755 0.05876 0.05066 0.0000 0.1855 1.0000
10.750 1.0576 0.06312 0.05530 0.0021 0.1837 1.0000
11.000 1.0202 0.06829 0.06069 0.0045 0.1845 1.0000
11.250 0.9642 0.07575 0.06822 0.0043 0.1880 1.0000
11.500 0.9180 0.08496 0.07745 0.0009 0.1907 1.0000
11.750 0.8867 0.09445 0.08692 -0.0033 0.1922 1.0000
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Polar data table (+)
Polar graphs
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