SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Reynolds number: 50,000 Max Cl/Cd: 28.66 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ssca09-il-50000.txt Download as CSV file: xf-ssca09-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SSC-A09 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5610 0.11281 0.10636 0.0168 1.0000 0.2621
-8.750 -0.5600 0.10962 0.10322 0.0164 1.0000 0.2785
-8.500 -0.5649 0.10685 0.10053 0.0156 1.0000 0.2951
-8.000 -0.5492 0.09995 0.09370 0.0177 1.0000 0.3391
-7.750 -0.5281 0.09572 0.08947 0.0196 1.0000 0.3633
-7.500 -0.5196 0.09245 0.08624 0.0210 1.0000 0.3900
-7.250 -0.5076 0.08923 0.08305 0.0228 1.0000 0.4206
-7.000 -0.5008 0.08660 0.08047 0.0250 1.0000 0.4557
-6.750 -0.4826 0.08308 0.07694 0.0271 1.0000 0.4910
-5.500 -0.5233 0.04841 0.04085 -0.0226 1.0000 0.1706
-5.250 -0.5045 0.04407 0.03578 -0.0221 1.0000 0.1414
-5.000 -0.4855 0.04067 0.03179 -0.0208 1.0000 0.1273
-4.750 -0.4648 0.03790 0.02830 -0.0192 1.0000 0.1179
-4.500 -0.4446 0.03528 0.02534 -0.0178 1.0000 0.1161
-4.250 -0.4229 0.03304 0.02267 -0.0165 1.0000 0.1163
-4.000 -0.3997 0.03095 0.02023 -0.0151 1.0000 0.1166
-3.750 -0.3752 0.02900 0.01796 -0.0138 1.0000 0.1167
-3.500 -0.3497 0.02732 0.01598 -0.0125 1.0000 0.1185
-3.250 -0.3245 0.02564 0.01433 -0.0114 1.0000 0.1264
-3.000 -0.1025 0.01949 0.01110 -0.0296 1.0000 1.0000
-2.750 -0.0901 0.01916 0.01046 -0.0282 1.0000 1.0000
-2.500 -0.0816 0.01891 0.01000 -0.0261 1.0000 1.0000
-2.250 -0.0768 0.01872 0.00963 -0.0233 1.0000 1.0000
-2.000 -0.0740 0.01857 0.00933 -0.0200 1.0000 1.0000
-1.750 -0.0717 0.01844 0.00905 -0.0166 1.0000 1.0000
-1.500 -0.0694 0.01832 0.00880 -0.0131 1.0000 1.0000
-1.250 -0.0663 0.01822 0.00857 -0.0097 1.0000 1.0000
-1.000 -0.0617 0.01814 0.00834 -0.0064 1.0000 1.0000
-0.750 -0.0552 0.01810 0.00816 -0.0035 1.0000 1.0000
-0.500 -0.0457 0.01810 0.00802 -0.0011 1.0000 1.0000
-0.250 -0.0328 0.01815 0.00794 0.0008 1.0000 1.0000
0.000 -0.0172 0.01826 0.00792 0.0021 1.0000 1.0000
0.250 0.0003 0.01841 0.00794 0.0031 1.0000 1.0000
0.500 0.0190 0.01861 0.00804 0.0038 1.0000 1.0000
0.750 0.0386 0.01885 0.00821 0.0044 1.0000 1.0000
1.000 0.0588 0.01913 0.00843 0.0048 1.0000 1.0000
1.250 0.0792 0.01946 0.00871 0.0051 1.0000 1.0000
1.500 0.0999 0.01983 0.00907 0.0053 1.0000 1.0000
1.750 0.1205 0.02026 0.00949 0.0054 1.0000 1.0000
2.000 0.1411 0.02075 0.01000 0.0053 1.0000 1.0000
2.250 0.1614 0.02130 0.01059 0.0052 1.0000 1.0000
2.500 0.1813 0.02194 0.01129 0.0050 1.0000 1.0000
2.750 0.2553 0.02325 0.01279 -0.0052 0.9758 1.0000
3.000 0.3482 0.02418 0.01406 -0.0173 0.9308 1.0000
3.250 0.4362 0.02391 0.01426 -0.0261 0.8809 1.0000
3.500 0.4941 0.02262 0.01334 -0.0271 0.8248 1.0000
3.750 0.5283 0.02074 0.01168 -0.0225 0.7500 1.0000
4.000 0.5514 0.01926 0.00986 -0.0156 0.6292 1.0000
4.250 0.5701 0.01989 0.00962 -0.0114 0.5291 1.0000
4.500 0.5928 0.02105 0.01030 -0.0098 0.4722 1.0000
4.750 0.6176 0.02218 0.01119 -0.0089 0.4349 1.0000
5.000 0.6437 0.02334 0.01219 -0.0083 0.4087 1.0000
5.250 0.6697 0.02451 0.01343 -0.0079 0.3863 1.0000
5.500 0.6956 0.02576 0.01463 -0.0075 0.3675 1.0000
5.750 0.7217 0.02713 0.01603 -0.0072 0.3514 1.0000
6.000 0.7466 0.02855 0.01765 -0.0069 0.3346 1.0000
6.250 0.7711 0.03010 0.01938 -0.0065 0.3183 1.0000
6.500 0.7945 0.03168 0.02116 -0.0061 0.3005 1.0000
6.750 0.8175 0.03337 0.02301 -0.0055 0.2827 1.0000
7.000 0.8401 0.03522 0.02496 -0.0049 0.2653 1.0000
7.250 0.8611 0.03725 0.02717 -0.0042 0.2468 1.0000
7.500 0.8796 0.03980 0.03011 -0.0034 0.2297 1.0000
7.750 0.8966 0.04230 0.03293 -0.0025 0.2119 1.0000
8.000 0.9120 0.04540 0.03635 -0.0016 0.1980 1.0000
8.250 0.9256 0.04831 0.03955 -0.0007 0.1835 1.0000
8.500 0.9396 0.05169 0.04317 0.0002 0.1734 1.0000
8.750 0.9564 0.05427 0.04578 0.0011 0.1610 1.0000
9.000 0.9455 0.06019 0.05245 0.0018 0.1578 1.0000
9.250 0.9339 0.06629 0.05897 0.0017 0.1567 1.0000
9.500 0.9179 0.07272 0.06566 0.0010 0.1574 1.0000
9.750 0.9003 0.07924 0.07232 -0.0004 0.1590 1.0000
10.000 0.8859 0.08546 0.07860 -0.0018 0.1604 1.0000
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Polar data table (+)
Polar graphs
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