S4053 (s4053-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4053 (s4053-il) Reynolds number: 50,000 Max Cl/Cd: 38.24 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4053-il-50000.txt Download as CSV file: xf-s4053-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S4053
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3783 0.09896 0.09228 -0.0219 1.0000 0.2372
-7.750 -0.3759 0.09592 0.08933 -0.0212 1.0000 0.2469
-7.500 -0.4002 0.09585 0.08946 -0.0211 1.0000 0.2552
-7.250 -0.3905 0.09223 0.08589 -0.0194 1.0000 0.2689
-7.000 -0.3837 0.08895 0.08265 -0.0177 1.0000 0.2818
-6.750 -0.3825 0.08619 0.07999 -0.0158 1.0000 0.2948
-6.500 -0.3858 0.08382 0.07774 -0.0137 1.0000 0.3090
-6.250 -0.3893 0.08156 0.07561 -0.0116 1.0000 0.3243
-6.000 -0.3991 0.07979 0.07397 -0.0095 1.0000 0.3413
-5.750 -0.4083 0.07785 0.07218 -0.0072 1.0000 0.3585
-5.500 -0.3954 0.07456 0.06893 -0.0031 1.0000 0.3804
-5.250 -0.4123 0.07336 0.06789 0.0002 1.0000 0.4026
-5.000 -0.4097 0.07102 0.06562 0.0047 1.0000 0.4288
-4.000 -0.3525 0.04576 0.03856 -0.0372 1.0000 0.1514
-3.750 -0.3262 0.04094 0.03292 -0.0388 1.0000 0.1275
-3.500 -0.3049 0.03822 0.02982 -0.0385 1.0000 0.1219
-3.250 -0.2826 0.03568 0.02684 -0.0383 1.0000 0.1203
-3.000 -0.2585 0.03338 0.02405 -0.0380 1.0000 0.1188
-2.750 -0.2337 0.03135 0.02153 -0.0375 1.0000 0.1166
-2.500 -0.2094 0.02968 0.01943 -0.0368 1.0000 0.1170
-2.250 -0.1857 0.02831 0.01775 -0.0359 1.0000 0.1195
-2.000 -0.1619 0.02718 0.01632 -0.0351 1.0000 0.1269
-1.750 -0.1399 0.02628 0.01530 -0.0341 1.0000 0.1399
-1.500 -0.1156 0.02519 0.01428 -0.0333 1.0000 0.1593
-1.250 -0.0797 0.02006 0.01271 -0.0324 1.0000 1.0000
-1.000 -0.0591 0.02044 0.01228 -0.0315 1.0000 1.0000
-0.750 -0.0397 0.02085 0.01222 -0.0309 1.0000 1.0000
-0.500 -0.0205 0.02130 0.01229 -0.0304 1.0000 1.0000
-0.250 -0.0015 0.02178 0.01246 -0.0300 1.0000 1.0000
0.000 0.0174 0.02230 0.01268 -0.0295 1.0000 1.0000
0.250 0.0362 0.02285 0.01300 -0.0292 1.0000 1.0000
0.500 0.0548 0.02345 0.01338 -0.0288 1.0000 1.0000
0.750 0.0732 0.02408 0.01382 -0.0285 1.0000 1.0000
1.000 0.1021 0.02501 0.01454 -0.0303 0.9955 1.0000
1.250 0.1473 0.02633 0.01567 -0.0351 0.9839 1.0000
1.500 0.1883 0.02747 0.01666 -0.0390 0.9718 1.0000
1.750 0.2265 0.02851 0.01759 -0.0424 0.9592 1.0000
2.000 0.2641 0.02954 0.01854 -0.0455 0.9462 1.0000
2.250 0.3011 0.03054 0.01950 -0.0485 0.9326 1.0000
2.500 0.3374 0.03153 0.02045 -0.0512 0.9188 1.0000
2.750 0.3739 0.03249 0.02141 -0.0538 0.9044 1.0000
3.000 0.4107 0.03343 0.02237 -0.0563 0.8895 1.0000
3.250 0.4490 0.03433 0.02334 -0.0588 0.8740 1.0000
3.500 0.4874 0.03518 0.02425 -0.0612 0.8581 1.0000
3.750 0.5148 0.03600 0.02515 -0.0618 0.8407 1.0000
4.000 0.5465 0.03678 0.02606 -0.0629 0.8226 1.0000
4.250 0.5852 0.03739 0.02681 -0.0647 0.8045 1.0000
4.500 0.6343 0.03765 0.02726 -0.0674 0.7866 1.0000
4.750 0.6561 0.03837 0.02811 -0.0665 0.7652 1.0000
5.000 0.7075 0.03806 0.02809 -0.0685 0.7451 1.0000
5.250 0.7421 0.03807 0.02832 -0.0684 0.7227 1.0000
5.500 0.8038 0.03640 0.02704 -0.0698 0.7014 1.0000
5.750 0.8394 0.03561 0.02650 -0.0684 0.6760 1.0000
6.000 0.8852 0.03375 0.02494 -0.0669 0.6488 1.0000
6.250 0.9330 0.03125 0.02275 -0.0650 0.6172 1.0000
6.500 0.9684 0.02939 0.02106 -0.0620 0.5787 1.0000
6.750 1.0002 0.02763 0.01933 -0.0586 0.5311 1.0000
7.000 1.0225 0.02674 0.01827 -0.0546 0.4719 1.0000
7.250 1.0353 0.02713 0.01828 -0.0504 0.4040 1.0000
7.500 1.0464 0.02845 0.01907 -0.0467 0.3383 1.0000
7.750 1.0597 0.03029 0.02042 -0.0440 0.2846 1.0000
8.000 1.0770 0.03237 0.02216 -0.0420 0.2432 1.0000
8.250 1.0969 0.03463 0.02435 -0.0406 0.2126 1.0000
8.500 1.1216 0.03709 0.02664 -0.0399 0.1885 1.0000
8.750 1.1391 0.03961 0.02944 -0.0383 0.1709 1.0000
9.000 1.1589 0.04255 0.03259 -0.0370 0.1572 1.0000
9.250 1.1748 0.04539 0.03561 -0.0355 0.1444 1.0000
9.500 1.1956 0.04895 0.03920 -0.0347 0.1337 1.0000
9.750 1.1934 0.05213 0.04315 -0.0311 0.1277 1.0000
10.000 1.2100 0.05601 0.04702 -0.0302 0.1198 1.0000
10.250 1.2009 0.05988 0.05155 -0.0267 0.1175 1.0000
10.500 1.1895 0.06386 0.05601 -0.0236 0.1153 1.0000
10.750 1.1759 0.06784 0.06034 -0.0208 0.1134 1.0000
11.000 1.1567 0.07195 0.06474 -0.0181 0.1130 1.0000
11.250 1.1298 0.07635 0.06936 -0.0157 0.1142 1.0000
11.500 1.1016 0.08144 0.07463 -0.0149 0.1163 1.0000
11.750 1.0764 0.08718 0.08048 -0.0156 0.1180 1.0000
12.000 1.0550 0.09349 0.08687 -0.0173 0.1192 1.0000
12.250 1.0369 0.10035 0.09378 -0.0196 0.1201 1.0000
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Polar data table (+)
Polar graphs
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