NACA 63A010 AIRFOIL (n63010a-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63A010 AIRFOIL (n63010a-il) Reynolds number: 50,000 Max Cl/Cd: 27.3 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63010a-il-50000.txt Download as CSV file: xf-n63010a-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63A010 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.7199 0.08048 0.07393 -0.0097 1.0000 0.1916
-8.250 -0.7403 0.07048 0.06369 -0.0157 1.0000 0.1559
-8.000 -0.7639 0.06330 0.05578 -0.0180 1.0000 0.1360
-7.750 -0.7546 0.05763 0.04991 -0.0178 1.0000 0.1272
-7.500 -0.7489 0.05287 0.04456 -0.0170 1.0000 0.1197
-7.250 -0.7377 0.04875 0.04003 -0.0159 1.0000 0.1175
-7.000 -0.7245 0.04509 0.03589 -0.0146 1.0000 0.1172
-6.750 -0.7082 0.04170 0.03201 -0.0133 1.0000 0.1172
-6.500 -0.6884 0.03844 0.02823 -0.0120 1.0000 0.1166
-6.250 -0.6658 0.03550 0.02484 -0.0108 1.0000 0.1173
-6.000 -0.6413 0.03297 0.02186 -0.0096 1.0000 0.1204
-5.750 -0.6160 0.03060 0.01939 -0.0089 1.0000 0.1289
-5.500 -0.5875 0.02844 0.01705 -0.0081 1.0000 0.1387
-5.250 -0.5594 0.02639 0.01509 -0.0073 1.0000 0.1554
-5.000 -0.5353 0.02443 0.01335 -0.0059 1.0000 0.1845
-4.750 -0.5197 0.02192 0.01151 -0.0038 1.0000 0.2517
-4.500 -0.5322 0.01949 0.01185 0.0067 1.0000 0.6274
-4.250 -0.5236 0.02124 0.01363 0.0172 1.0000 0.7425
-4.000 -0.4847 0.02385 0.01584 0.0244 1.0000 0.8182
-3.750 -0.3455 0.02666 0.01755 0.0139 1.0000 0.9020
-3.500 -0.2852 0.02591 0.01635 0.0076 1.0000 0.9303
-3.250 -0.2317 0.02497 0.01508 0.0016 1.0000 0.9539
-3.000 -0.1737 0.02382 0.01362 -0.0057 1.0000 0.9734
-2.750 -0.1182 0.02263 0.01221 -0.0129 1.0000 0.9911
-2.500 -0.0797 0.02167 0.01112 -0.0171 1.0000 1.0000
-2.250 -0.0627 0.02104 0.01043 -0.0171 1.0000 1.0000
-2.000 -0.0461 0.02048 0.00983 -0.0170 1.0000 1.0000
-1.750 -0.0299 0.01997 0.00931 -0.0167 1.0000 1.0000
-1.500 -0.0147 0.01953 0.00886 -0.0162 1.0000 1.0000
-1.250 -0.0008 0.01914 0.00849 -0.0154 1.0000 1.0000
-1.000 0.0107 0.01882 0.00820 -0.0142 1.0000 1.0000
-0.750 0.0181 0.01858 0.00800 -0.0122 1.0000 1.0000
-0.500 0.0187 0.01844 0.00791 -0.0092 1.0000 1.0000
-0.250 0.0122 0.01837 0.00788 -0.0050 1.0000 1.0000
0.000 0.0000 0.01835 0.00788 0.0000 1.0000 1.0000
0.250 -0.0121 0.01837 0.00788 0.0050 1.0000 1.0000
0.500 -0.0187 0.01843 0.00791 0.0092 1.0000 1.0000
0.750 -0.0180 0.01858 0.00800 0.0122 1.0000 1.0000
1.000 -0.0106 0.01882 0.00820 0.0142 1.0000 1.0000
1.250 0.0009 0.01914 0.00849 0.0154 1.0000 1.0000
1.500 0.0147 0.01952 0.00885 0.0162 1.0000 1.0000
1.750 0.0300 0.01997 0.00930 0.0167 1.0000 1.0000
2.000 0.0462 0.02047 0.00982 0.0170 1.0000 1.0000
2.250 0.0629 0.02104 0.01042 0.0171 1.0000 1.0000
2.500 0.0799 0.02166 0.01111 0.0171 1.0000 1.0000
2.750 0.1183 0.02262 0.01220 0.0129 0.9912 1.0000
3.000 0.1738 0.02381 0.01361 0.0057 0.9734 1.0000
3.250 0.2319 0.02497 0.01508 -0.0016 0.9539 1.0000
3.500 0.2853 0.02591 0.01634 -0.0076 0.9303 1.0000
3.750 0.3457 0.02665 0.01754 -0.0140 0.9020 1.0000
4.000 0.4847 0.02384 0.01584 -0.0243 0.8182 1.0000
4.250 0.5235 0.02124 0.01363 -0.0172 0.7426 1.0000
4.500 0.5321 0.01949 0.01186 -0.0067 0.6278 1.0000
4.750 0.5197 0.02191 0.01151 0.0038 0.2518 1.0000
5.000 0.5352 0.02443 0.01335 0.0059 0.1845 1.0000
5.250 0.5593 0.02639 0.01509 0.0073 0.1554 1.0000
5.500 0.5874 0.02844 0.01704 0.0081 0.1387 1.0000
5.750 0.6159 0.03060 0.01939 0.0089 0.1289 1.0000
6.000 0.6412 0.03297 0.02186 0.0097 0.1204 1.0000
6.250 0.6657 0.03550 0.02484 0.0108 0.1173 1.0000
6.500 0.6884 0.03844 0.02823 0.0120 0.1166 1.0000
6.750 0.7082 0.04170 0.03201 0.0133 0.1172 1.0000
7.000 0.7245 0.04509 0.03590 0.0146 0.1172 1.0000
7.250 0.7377 0.04876 0.04004 0.0159 0.1175 1.0000
7.500 0.7490 0.05288 0.04457 0.0169 0.1197 1.0000
7.750 0.7546 0.05765 0.04993 0.0178 0.1273 1.0000
8.000 0.7642 0.06332 0.05580 0.0179 0.1361 1.0000
8.250 0.7403 0.07053 0.06375 0.0156 0.1560 1.0000
8.500 0.7081 0.08008 0.07354 0.0088 0.1847 1.0000
8.750 0.6108 0.10385 0.09701 -0.0265 0.3790 1.0000
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Polar data table (+)
Polar graphs
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