S1012 (s1012-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1012 (s1012-il) Reynolds number: 50,000 Max Cl/Cd: 26.21 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1012-il-50000.txt Download as CSV file: xf-s1012-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S1012
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 -0.4897 0.11129 0.10345 0.0007 1.0000 0.3841
-10.000 -0.6990 0.07928 0.07189 -0.0334 1.0000 0.1880
-9.750 -0.7166 0.07393 0.06650 -0.0336 1.0000 0.1836
-9.500 -0.7406 0.06921 0.06175 -0.0322 1.0000 0.1808
-9.250 -0.8096 0.06314 0.05524 -0.0281 1.0000 0.1720
-9.000 -0.8252 0.05945 0.05124 -0.0247 1.0000 0.1709
-8.750 -0.8054 0.05682 0.04878 -0.0238 1.0000 0.1770
-8.500 -0.8144 0.05394 0.04569 -0.0201 1.0000 0.1788
-8.250 -0.8233 0.05122 0.04270 -0.0160 1.0000 0.1804
-8.000 -0.8307 0.04854 0.03968 -0.0118 1.0000 0.1822
-7.750 -0.8358 0.04597 0.03669 -0.0076 1.0000 0.1843
-7.500 -0.8331 0.04359 0.03402 -0.0043 1.0000 0.1889
-7.250 -0.8218 0.04171 0.03208 -0.0020 1.0000 0.1956
-7.000 -0.8164 0.03952 0.02941 0.0012 1.0000 0.2005
-6.750 -0.8025 0.03755 0.02737 0.0032 1.0000 0.2078
-6.500 -0.7913 0.03586 0.02529 0.0058 1.0000 0.2169
-6.250 -0.7729 0.03407 0.02350 0.0072 1.0000 0.2258
-6.000 -0.7565 0.03249 0.02170 0.0090 1.0000 0.2372
-5.750 -0.7387 0.03108 0.02011 0.0107 1.0000 0.2507
-5.500 -0.7185 0.02970 0.01867 0.0121 1.0000 0.2659
-5.250 -0.6966 0.02841 0.01750 0.0132 1.0000 0.2850
-5.000 -0.6737 0.02720 0.01636 0.0143 1.0000 0.3083
-4.750 -0.6509 0.02603 0.01539 0.0154 1.0000 0.3391
-4.500 -0.6289 0.02481 0.01447 0.0167 1.0000 0.3810
-4.250 -0.6122 0.02337 0.01365 0.0191 1.0000 0.4464
-4.000 -0.5839 0.02340 0.01564 0.0248 1.0000 0.6587
-3.750 -0.5618 0.02645 0.01854 0.0325 1.0000 0.7914
-3.500 -0.4092 0.03113 0.02239 0.0201 1.0000 0.8789
-3.250 -0.2330 0.03161 0.02216 -0.0031 1.0000 0.9421
-3.000 -0.0578 0.02879 0.01880 -0.0311 1.0000 1.0000
-2.750 -0.0566 0.02850 0.01844 -0.0285 1.0000 1.0000
-2.500 -0.0545 0.02826 0.01814 -0.0258 1.0000 1.0000
-2.250 -0.0515 0.02806 0.01787 -0.0231 1.0000 1.0000
-2.000 -0.0477 0.02789 0.01764 -0.0205 1.0000 1.0000
-1.750 -0.0432 0.02774 0.01744 -0.0179 1.0000 1.0000
-1.500 -0.0380 0.02762 0.01727 -0.0153 1.0000 1.0000
-1.250 -0.0324 0.02752 0.01713 -0.0127 1.0000 1.0000
-1.000 -0.0264 0.02743 0.01702 -0.0101 1.0000 1.0000
-0.750 -0.0200 0.02737 0.01693 -0.0076 1.0000 1.0000
-0.500 -0.0135 0.02732 0.01686 -0.0051 1.0000 1.0000
-0.250 -0.0068 0.02730 0.01683 -0.0025 1.0000 1.0000
0.000 0.0000 0.02729 0.01681 0.0000 1.0000 1.0000
0.250 0.0068 0.02730 0.01683 0.0025 1.0000 1.0000
0.500 0.0135 0.02732 0.01686 0.0051 1.0000 1.0000
0.750 0.0201 0.02737 0.01692 0.0076 1.0000 1.0000
1.000 0.0264 0.02743 0.01701 0.0101 1.0000 1.0000
1.250 0.0324 0.02751 0.01712 0.0127 1.0000 1.0000
1.500 0.0381 0.02761 0.01726 0.0153 1.0000 1.0000
1.750 0.0432 0.02773 0.01744 0.0179 1.0000 1.0000
2.000 0.0477 0.02788 0.01763 0.0205 1.0000 1.0000
2.250 0.0515 0.02805 0.01786 0.0231 1.0000 1.0000
2.500 0.0545 0.02825 0.01812 0.0258 1.0000 1.0000
2.750 0.0566 0.02849 0.01842 0.0285 1.0000 1.0000
3.000 0.0577 0.02877 0.01878 0.0311 1.0000 1.0000
3.250 0.2308 0.03157 0.02211 0.0035 0.9425 1.0000
3.500 0.4091 0.03112 0.02238 -0.0201 0.8788 1.0000
3.750 0.5616 0.02645 0.01854 -0.0325 0.7917 1.0000
4.000 0.5838 0.02340 0.01564 -0.0248 0.6594 1.0000
4.250 0.6122 0.02336 0.01365 -0.0191 0.4465 1.0000
4.500 0.6289 0.02481 0.01447 -0.0167 0.3809 1.0000
4.750 0.6508 0.02603 0.01538 -0.0154 0.3390 1.0000
5.000 0.6736 0.02720 0.01636 -0.0142 0.3081 1.0000
5.250 0.6965 0.02840 0.01750 -0.0132 0.2849 1.0000
5.500 0.7185 0.02971 0.01867 -0.0121 0.2657 1.0000
5.750 0.7386 0.03107 0.02011 -0.0107 0.2507 1.0000
6.000 0.7564 0.03248 0.02169 -0.0090 0.2371 1.0000
6.250 0.7729 0.03407 0.02350 -0.0072 0.2258 1.0000
6.500 0.7913 0.03586 0.02529 -0.0057 0.2169 1.0000
6.750 0.8025 0.03755 0.02737 -0.0032 0.2079 1.0000
7.000 0.8164 0.03952 0.02941 -0.0012 0.2005 1.0000
7.250 0.8217 0.04171 0.03207 0.0020 0.1954 1.0000
7.500 0.8338 0.04356 0.03396 0.0042 0.1886 1.0000
7.750 0.8358 0.04596 0.03668 0.0076 0.1843 1.0000
8.000 0.8306 0.04853 0.03968 0.0118 0.1821 1.0000
8.250 0.8234 0.05120 0.04268 0.0160 0.1805 1.0000
8.500 0.8143 0.05395 0.04569 0.0201 0.1788 1.0000
8.750 0.8064 0.05676 0.04870 0.0238 0.1767 1.0000
9.000 0.8249 0.05944 0.05123 0.0248 0.1709 1.0000
9.250 0.8087 0.06315 0.05527 0.0281 0.1720 1.0000
9.500 0.7409 0.06922 0.06176 0.0321 0.1808 1.0000
9.750 0.7172 0.07396 0.06653 0.0335 0.1837 1.0000
10.000 0.6499 0.08374 0.07628 0.0297 0.1997 1.0000
10.250 0.6634 0.08861 0.08118 0.0295 0.2022 1.0000
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Polar data table (+)
Polar graphs
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