S8038 (13%) (s8038-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8038 (13%) (s8038-il) Reynolds number: 50,000 Max Cl/Cd: 29.24 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8038-il-50000.txt Download as CSV file: xf-s8038-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S8038 (13%)
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5624 0.09218 0.08497 -0.0334 1.0000 0.1337
-10.000 -0.5875 0.08311 0.07596 -0.0391 1.0000 0.1250
-9.750 -0.7009 0.07410 0.06679 -0.0430 1.0000 0.1163
-9.500 -0.6972 0.06961 0.06231 -0.0422 1.0000 0.1147
-9.250 -0.7087 0.06549 0.05810 -0.0406 1.0000 0.1132
-9.000 -0.7221 0.06146 0.05391 -0.0384 1.0000 0.1116
-8.750 -0.7344 0.05747 0.04966 -0.0358 1.0000 0.1101
-8.500 -0.7418 0.05365 0.04552 -0.0331 1.0000 0.1091
-8.250 -0.7435 0.05022 0.04176 -0.0303 1.0000 0.1092
-8.000 -0.7410 0.04712 0.03829 -0.0276 1.0000 0.1107
-7.750 -0.7360 0.04421 0.03497 -0.0249 1.0000 0.1129
-7.500 -0.7284 0.04147 0.03173 -0.0221 1.0000 0.1152
-7.250 -0.7140 0.03861 0.02865 -0.0202 1.0000 0.1187
-7.000 -0.6955 0.03627 0.02623 -0.0185 1.0000 0.1242
-6.750 -0.6789 0.03409 0.02374 -0.0164 1.0000 0.1323
-6.500 -0.6607 0.03221 0.02172 -0.0145 1.0000 0.1453
-6.250 -0.6413 0.03024 0.02004 -0.0129 1.0000 0.1653
-6.000 -0.6257 0.02847 0.01849 -0.0106 1.0000 0.1959
-5.750 -0.6142 0.02670 0.01711 -0.0077 1.0000 0.2422
-5.500 -0.6074 0.02495 0.01589 -0.0039 1.0000 0.3110
-5.250 -0.6028 0.02359 0.01528 0.0006 1.0000 0.3949
-5.000 -0.5974 0.02312 0.01541 0.0057 1.0000 0.4796
-4.750 -0.5891 0.02346 0.01607 0.0112 1.0000 0.5497
-4.500 -0.5793 0.02403 0.01676 0.0166 1.0000 0.6061
-4.250 -0.5675 0.02469 0.01747 0.0219 1.0000 0.6524
-4.000 -0.5543 0.02534 0.01812 0.0271 1.0000 0.6931
-3.750 -0.5412 0.02583 0.01855 0.0320 1.0000 0.7310
-3.500 -0.5287 0.02611 0.01872 0.0365 1.0000 0.7672
-3.250 -0.5051 0.02665 0.01914 0.0397 1.0000 0.8011
-3.000 -0.4670 0.02732 0.01960 0.0402 1.0000 0.8353
-2.750 -0.4007 0.02817 0.02012 0.0355 1.0000 0.8688
-2.500 -0.3044 0.02883 0.02035 0.0245 1.0000 0.8991
-2.250 -0.2300 0.02886 0.02009 0.0158 1.0000 0.9262
-2.000 -0.1505 0.02858 0.01955 0.0054 1.0000 0.9502
-1.750 -0.0861 0.02816 0.01894 -0.0032 1.0000 0.9724
-1.500 -0.0160 0.02759 0.01821 -0.0134 1.0000 0.9938
-1.250 -0.0018 0.02742 0.01799 -0.0144 1.0000 1.0000
-1.000 -0.0154 0.02751 0.01810 -0.0106 1.0000 1.0000
-0.750 -0.0285 0.02754 0.01812 -0.0070 1.0000 1.0000
-0.500 -0.0415 0.02751 0.01807 -0.0035 1.0000 1.0000
-0.250 -0.0548 0.02741 0.01795 0.0002 1.0000 1.0000
0.000 -0.0686 0.02722 0.01774 0.0040 1.0000 1.0000
0.250 -0.0382 0.02757 0.01805 0.0003 0.9896 1.0000
0.500 0.0108 0.02817 0.01858 -0.0062 0.9733 1.0000
0.750 0.0562 0.02868 0.01905 -0.0117 0.9569 1.0000
1.000 0.0921 0.02907 0.01941 -0.0153 0.9398 1.0000
1.250 0.1274 0.02948 0.01979 -0.0184 0.9227 1.0000
1.500 0.1629 0.02991 0.02020 -0.0213 0.9055 1.0000
1.750 0.1996 0.03033 0.02063 -0.0241 0.8880 1.0000
2.000 0.2396 0.03074 0.02104 -0.0271 0.8703 1.0000
2.250 0.2845 0.03107 0.02142 -0.0305 0.8526 1.0000
2.500 0.3404 0.03121 0.02165 -0.0353 0.8349 1.0000
2.750 0.3683 0.03152 0.02199 -0.0355 0.8149 1.0000
3.000 0.4128 0.03153 0.02210 -0.0379 0.7943 1.0000
3.250 0.4781 0.03081 0.02154 -0.0423 0.7734 1.0000
3.500 0.5148 0.03052 0.02134 -0.0423 0.7510 1.0000
3.750 0.5536 0.02998 0.02089 -0.0422 0.7277 1.0000
4.000 0.5891 0.02941 0.02040 -0.0414 0.7038 1.0000
4.250 0.6230 0.02874 0.01979 -0.0400 0.6787 1.0000
4.500 0.6452 0.02849 0.01957 -0.0374 0.6520 1.0000
4.750 0.6734 0.02792 0.01899 -0.0351 0.6239 1.0000
5.000 0.6991 0.02742 0.01847 -0.0326 0.5933 1.0000
5.250 0.7212 0.02707 0.01806 -0.0297 0.5600 1.0000
5.500 0.7430 0.02680 0.01767 -0.0268 0.5244 1.0000
5.750 0.7649 0.02661 0.01728 -0.0240 0.4870 1.0000
6.000 0.7803 0.02694 0.01745 -0.0208 0.4489 1.0000
6.250 0.7990 0.02733 0.01757 -0.0182 0.4130 1.0000
6.500 0.8173 0.02804 0.01804 -0.0159 0.3806 1.0000
6.750 0.8332 0.02901 0.01889 -0.0135 0.3519 1.0000
7.000 0.8502 0.03022 0.02004 -0.0115 0.3279 1.0000
7.250 0.8696 0.03141 0.02111 -0.0099 0.3066 1.0000
7.500 0.8917 0.03272 0.02225 -0.0088 0.2882 1.0000
7.750 0.9102 0.03432 0.02391 -0.0074 0.2736 1.0000
8.000 0.9251 0.03603 0.02578 -0.0055 0.2605 1.0000
8.250 0.9391 0.03785 0.02777 -0.0036 0.2485 1.0000
8.500 0.9560 0.03987 0.02988 -0.0022 0.2391 1.0000
8.750 0.9701 0.04196 0.03218 -0.0005 0.2306 1.0000
9.000 0.9783 0.04441 0.03487 0.0016 0.2233 1.0000
9.250 0.9908 0.04652 0.03712 0.0033 0.2153 1.0000
9.500 0.9975 0.04943 0.04023 0.0053 0.2103 1.0000
9.750 0.9856 0.05301 0.04425 0.0087 0.2075 1.0000
10.000 0.9713 0.05676 0.04830 0.0118 0.2049 1.0000
10.250 0.9538 0.06069 0.05246 0.0146 0.2028 1.0000
10.500 0.9343 0.06467 0.05659 0.0171 0.2009 1.0000
10.750 0.9142 0.06876 0.06076 0.0193 0.1993 1.0000
11.000 0.8983 0.07339 0.06545 0.0202 0.1979 1.0000
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Polar data table (+)
Polar graphs
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