NACA 16-006 (naca16006-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 16-006 (naca16006-il) Reynolds number: 1,000,000 Max Cl/Cd: 40.83 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16006-il-1000000.txt Download as CSV file: xf-naca16006-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-006
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5253 0.08273 0.08117 -0.0118 1.0000 0.0062
-8.750 -0.5299 0.07788 0.07633 -0.0137 1.0000 0.0062
-8.500 -0.5364 0.07280 0.07126 -0.0162 1.0000 0.0062
-8.250 -0.5474 0.06728 0.06575 -0.0210 1.0000 0.0062
-8.000 -0.5605 0.06277 0.06121 -0.0230 1.0000 0.0062
-7.750 -0.5714 0.05860 0.05700 -0.0228 1.0000 0.0062
-7.500 -0.5772 0.05412 0.05245 -0.0224 1.0000 0.0062
-7.250 -0.5819 0.04977 0.04803 -0.0212 1.0000 0.0062
-7.000 -0.5850 0.04559 0.04377 -0.0194 1.0000 0.0062
-6.750 -0.5868 0.04165 0.03973 -0.0170 1.0000 0.0062
-6.500 -0.5879 0.03779 0.03575 -0.0142 1.0000 0.0062
-6.250 -0.5878 0.03409 0.03193 -0.0111 1.0000 0.0063
-6.000 -0.5861 0.03060 0.02829 -0.0079 1.0000 0.0063
-5.750 -0.5830 0.02720 0.02472 -0.0046 1.0000 0.0063
-5.500 -0.5785 0.02385 0.02118 -0.0013 1.0000 0.0063
-5.000 -0.5839 0.02435 0.02060 0.0063 0.9991 0.0055
-4.750 -0.5590 0.01954 0.01526 0.0077 0.9979 0.0057
-4.500 -0.5338 0.01576 0.01095 0.0086 0.9969 0.0070
-4.250 -0.5055 0.01402 0.00900 0.0085 0.9962 0.0075
-4.000 -0.4759 0.01292 0.00776 0.0080 0.9954 0.0081
-3.750 -0.4448 0.01245 0.00723 0.0070 0.9947 0.0093
-3.500 -0.4171 0.01063 0.00523 0.0073 0.9942 0.0089
-3.250 -0.3902 0.00956 0.00399 0.0076 0.9930 0.0094
-3.000 -0.3613 0.00907 0.00345 0.0073 0.9913 0.0116
-2.750 -0.3307 0.00885 0.00320 0.0065 0.9897 0.0127
-2.500 -0.3013 0.00817 0.00242 0.0061 0.9881 0.0188
-2.250 -0.2698 0.00793 0.00218 0.0051 0.9867 0.0299
-2.000 -0.2375 0.00775 0.00199 0.0039 0.9854 0.0378
-1.750 -0.2071 0.00713 0.00178 0.0029 0.9843 0.1579
-1.500 -0.1831 0.00548 0.00157 0.0025 0.9833 0.5665
-1.250 -0.1588 0.00448 0.00154 0.0031 0.9822 0.8299
-1.000 -0.1320 0.00435 0.00158 0.0035 0.9797 0.8848
-0.750 -0.1037 0.00432 0.00161 0.0035 0.9767 0.9142
-0.500 -0.0727 0.00434 0.00167 0.0030 0.9745 0.9383
-0.250 -0.0399 0.00449 0.00186 0.0023 0.9729 0.9612
0.000 0.0000 0.00463 0.00200 0.0000 0.9714 0.9714
0.250 0.0398 0.00449 0.00186 -0.0023 0.9612 0.9729
0.500 0.0727 0.00434 0.00167 -0.0029 0.9384 0.9745
0.750 0.1036 0.00432 0.00161 -0.0034 0.9143 0.9768
1.000 0.1318 0.00435 0.00158 -0.0034 0.8857 0.9798
1.250 0.1588 0.00448 0.00154 -0.0031 0.8293 0.9822
1.500 0.1831 0.00548 0.00156 -0.0025 0.5672 0.9833
1.750 0.2071 0.00713 0.00178 -0.0029 0.1581 0.9843
2.000 0.2376 0.00775 0.00199 -0.0040 0.0376 0.9855
2.250 0.2698 0.00792 0.00218 -0.0051 0.0299 0.9868
2.500 0.3013 0.00817 0.00241 -0.0061 0.0186 0.9882
2.750 0.3308 0.00885 0.00320 -0.0066 0.0127 0.9898
3.000 0.3613 0.00907 0.00345 -0.0073 0.0116 0.9914
3.250 0.3903 0.00956 0.00399 -0.0076 0.0094 0.9931
3.500 0.4173 0.01064 0.00523 -0.0074 0.0089 0.9943
3.750 0.4451 0.01243 0.00721 -0.0071 0.0092 0.9947
4.000 0.4761 0.01291 0.00775 -0.0080 0.0081 0.9955
4.250 0.5057 0.01400 0.00898 -0.0085 0.0075 0.9963
4.500 0.5340 0.01576 0.01095 -0.0087 0.0070 0.9971
4.750 0.5593 0.01954 0.01526 -0.0078 0.0057 0.9980
5.000 0.5843 0.02442 0.02068 -0.0063 0.0055 0.9992
5.250 0.5897 0.03244 0.02930 -0.0027 0.0063 1.0000
5.500 0.5985 0.03587 0.03296 0.0006 0.0063 1.0000
5.750 0.6061 0.03932 0.03661 0.0039 0.0063 1.0000
6.000 0.6126 0.04279 0.04026 0.0071 0.0063 1.0000
6.250 0.6180 0.04630 0.04393 0.0101 0.0062 1.0000
6.500 0.6226 0.04990 0.04767 0.0129 0.0062 1.0000
6.750 0.6267 0.05361 0.05151 0.0152 0.0062 1.0000
7.000 0.6304 0.05747 0.05548 0.0170 0.0062 1.0000
7.250 0.6335 0.06148 0.05962 0.0182 0.0062 1.0000
7.500 0.6362 0.06570 0.06393 0.0186 0.0062 1.0000
7.750 0.6386 0.07014 0.06844 0.0180 0.0062 1.0000
8.000 0.6400 0.07476 0.07313 0.0165 0.0062 1.0000
8.250 0.6392 0.07942 0.07783 0.0143 0.0062 1.0000
8.500 0.6341 0.08415 0.08258 0.0107 0.0062 1.0000
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Polar data table (+)
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