S4083 (8%) (s4083-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4083 (8%) (s4083-il) Reynolds number: 500,000 Max Cl/Cd: 98.48 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4083-il-500000-n5.txt Download as CSV file: xf-s4083-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4083 (8%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3838 0.08797 0.08579 -0.0183 1.0000 0.0103
-7.500 -0.3855 0.08511 0.08297 -0.0184 1.0000 0.0103
-7.250 -0.3904 0.08236 0.08027 -0.0180 1.0000 0.0103
-7.000 -0.3888 0.07906 0.07700 -0.0192 1.0000 0.0103
-6.750 -0.3854 0.07552 0.07349 -0.0212 1.0000 0.0103
-6.500 -0.3635 0.07000 0.06796 -0.0288 0.9977 0.0103
-6.250 -0.3359 0.06388 0.06179 -0.0380 0.9943 0.0103
-5.250 -0.2223 0.03089 0.02795 -0.0709 0.9665 0.0065
-5.000 -0.1934 0.02218 0.01845 -0.0742 0.9584 0.0066
-4.750 -0.1629 0.01808 0.01369 -0.0757 0.9505 0.0068
-4.500 -0.1320 0.01530 0.01042 -0.0769 0.9408 0.0072
-4.250 -0.0935 0.01382 0.00866 -0.0793 0.9294 0.0075
-4.000 -0.0429 0.01277 0.00741 -0.0844 0.9146 0.0081
-3.750 0.0159 0.01178 0.00613 -0.0912 0.8838 0.0090
-3.500 0.0559 0.01096 0.00493 -0.0936 0.8293 0.0091
-3.250 0.0812 0.01056 0.00420 -0.0928 0.7757 0.0091
-3.000 0.1043 0.01026 0.00362 -0.0915 0.7303 0.0092
-2.750 0.1276 0.01002 0.00312 -0.0904 0.6907 0.0095
-2.500 0.1517 0.00983 0.00273 -0.0894 0.6569 0.0097
-2.250 0.1765 0.00970 0.00239 -0.0886 0.6275 0.0101
-2.000 0.2017 0.00955 0.00207 -0.0878 0.6026 0.0111
-1.750 0.2273 0.00944 0.00184 -0.0872 0.5806 0.0141
-1.500 0.2531 0.00931 0.00166 -0.0866 0.5616 0.0278
-1.250 0.2787 0.00911 0.00155 -0.0862 0.5436 0.0747
-1.000 0.3044 0.00892 0.00148 -0.0857 0.5278 0.1378
-0.750 0.3298 0.00866 0.00144 -0.0853 0.5134 0.2388
-0.500 0.3551 0.00842 0.00143 -0.0849 0.4997 0.3414
-0.250 0.3804 0.00821 0.00145 -0.0844 0.4872 0.4466
0.000 0.4052 0.00800 0.00149 -0.0838 0.4763 0.5566
0.250 0.4297 0.00785 0.00153 -0.0830 0.4656 0.6514
0.500 0.4538 0.00769 0.00155 -0.0821 0.4551 0.7296
1.000 0.5258 0.00737 0.00159 -0.0853 0.4345 1.0000
1.250 0.5521 0.00749 0.00162 -0.0849 0.4249 1.0000
1.500 0.5785 0.00760 0.00166 -0.0845 0.4157 1.0000
1.750 0.6048 0.00772 0.00171 -0.0840 0.4062 1.0000
2.000 0.6310 0.00785 0.00178 -0.0836 0.3966 1.0000
2.250 0.6574 0.00797 0.00184 -0.0832 0.3880 1.0000
2.500 0.6835 0.00811 0.00192 -0.0828 0.3800 1.0000
2.750 0.7100 0.00823 0.00201 -0.0824 0.3720 1.0000
3.000 0.7362 0.00837 0.00212 -0.0820 0.3641 1.0000
3.250 0.7624 0.00850 0.00223 -0.0816 0.3560 1.0000
3.500 0.7886 0.00864 0.00234 -0.0812 0.3480 1.0000
3.750 0.8146 0.00880 0.00247 -0.0807 0.3391 1.0000
4.000 0.8407 0.00895 0.00262 -0.0803 0.3296 1.0000
4.250 0.8666 0.00912 0.00276 -0.0799 0.3206 1.0000
4.500 0.8924 0.00929 0.00291 -0.0795 0.3113 1.0000
4.750 0.9184 0.00945 0.00308 -0.0791 0.3026 1.0000
5.000 0.9440 0.00965 0.00328 -0.0786 0.2915 1.0000
5.250 0.9694 0.00986 0.00347 -0.0781 0.2792 1.0000
5.500 0.9946 0.01010 0.00368 -0.0776 0.2669 1.0000
6.000 1.0442 0.01064 0.00415 -0.0765 0.2350 1.0000
6.250 1.0674 0.01108 0.00448 -0.0757 0.2042 1.0000
6.500 1.0907 0.01152 0.00482 -0.0750 0.1804 1.0000
6.750 1.1119 0.01219 0.00528 -0.0740 0.1430 1.0000
7.000 1.1324 0.01293 0.00582 -0.0729 0.1068 1.0000
7.250 1.1541 0.01353 0.00633 -0.0720 0.0835 1.0000
7.500 1.1752 0.01417 0.00688 -0.0709 0.0621 1.0000
7.750 1.1942 0.01505 0.00759 -0.0696 0.0351 1.0000
8.000 1.2115 0.01608 0.00848 -0.0680 0.0118 1.0000
8.250 1.2316 0.01677 0.00918 -0.0668 0.0068 1.0000
8.500 1.2525 0.01737 0.00984 -0.0657 0.0055 1.0000
8.750 1.2733 0.01794 0.01052 -0.0646 0.0052 1.0000
9.000 1.2935 0.01856 0.01123 -0.0634 0.0048 1.0000
9.250 1.3125 0.01926 0.01203 -0.0621 0.0044 1.0000
9.500 1.3308 0.01999 0.01287 -0.0606 0.0042 1.0000
9.750 1.3476 0.02084 0.01382 -0.0590 0.0040 1.0000
10.000 1.3623 0.02181 0.01492 -0.0571 0.0038 1.0000
10.250 1.3752 0.02286 0.01609 -0.0550 0.0037 1.0000
10.500 1.3826 0.02425 0.01764 -0.0522 0.0035 1.0000
10.750 1.3895 0.02543 0.01896 -0.0492 0.0035 1.0000
11.000 1.3944 0.02655 0.02019 -0.0460 0.0035 1.0000
11.250 1.3971 0.02782 0.02159 -0.0427 0.0034 1.0000
11.500 1.3983 0.02924 0.02312 -0.0396 0.0034 1.0000
11.750 1.3974 0.03089 0.02490 -0.0366 0.0034 1.0000
12.000 1.3952 0.03279 0.02694 -0.0342 0.0034 1.0000
12.250 1.3914 0.03506 0.02935 -0.0323 0.0034 1.0000
12.500 1.3872 0.03768 0.03210 -0.0311 0.0033 1.0000
12.750 1.3827 0.04068 0.03525 -0.0306 0.0033 1.0000
13.000 1.3773 0.04417 0.03889 -0.0309 0.0033 1.0000
13.250 1.3727 0.04786 0.04271 -0.0316 0.0033 1.0000
13.500 1.3682 0.05175 0.04674 -0.0327 0.0032 1.0000
13.750 1.3594 0.05639 0.05153 -0.0342 0.0032 1.0000
14.000 1.3531 0.06082 0.05610 -0.0357 0.0032 1.0000
14.250 1.3451 0.06558 0.06099 -0.0375 0.0032 1.0000
14.500 1.3361 0.07058 0.06612 -0.0394 0.0031 1.0000
14.750 1.3287 0.07548 0.07114 -0.0414 0.0031 1.0000
15.000 1.3174 0.08103 0.07683 -0.0436 0.0030 1.0000
15.250 1.3069 0.08666 0.08259 -0.0461 0.0030 1.0000
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Polar data table (+)
Polar graphs
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