NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-209 (naca64209-il) Reynolds number: 50,000 Max Cl/Cd: 32 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64209-il-50000-n5.txt Download as CSV file: xf-naca64209-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5549 0.09730 0.09025 -0.0187 1.0000 0.0546
-9.250 -0.5567 0.09226 0.08528 -0.0217 1.0000 0.0531
-9.000 -0.5630 0.08614 0.07923 -0.0265 1.0000 0.0511
-8.750 -0.5891 0.07883 0.07188 -0.0343 1.0000 0.0475
-8.500 -0.5918 0.07457 0.06759 -0.0357 1.0000 0.0471
-8.250 -0.5956 0.07026 0.06319 -0.0371 1.0000 0.0470
-8.000 -0.5980 0.06596 0.05873 -0.0382 1.0000 0.0469
-7.750 -0.5987 0.06170 0.05421 -0.0389 1.0000 0.0471
-7.500 -0.5964 0.05756 0.04971 -0.0393 1.0000 0.0475
-7.250 -0.5907 0.05363 0.04532 -0.0391 1.0000 0.0479
-7.000 -0.5802 0.04972 0.04116 -0.0388 1.0000 0.0484
-6.750 -0.5675 0.04605 0.03708 -0.0382 1.0000 0.0484
-6.500 -0.5526 0.04263 0.03331 -0.0375 1.0000 0.0489
-6.250 -0.5357 0.03957 0.02993 -0.0367 1.0000 0.0496
-6.000 -0.5174 0.03680 0.02684 -0.0358 1.0000 0.0509
-5.750 -0.4981 0.03451 0.02418 -0.0348 1.0000 0.0540
-5.500 -0.4771 0.03232 0.02144 -0.0336 1.0000 0.0582
-5.250 -0.4566 0.03024 0.01926 -0.0327 1.0000 0.0623
-5.000 -0.4351 0.02870 0.01748 -0.0315 1.0000 0.0682
-4.750 -0.4146 0.02727 0.01597 -0.0304 1.0000 0.0765
-4.500 -0.3930 0.02604 0.01458 -0.0290 1.0000 0.0811
-4.250 -0.3719 0.02497 0.01333 -0.0273 1.0000 0.0829
-4.000 -0.3520 0.02410 0.01224 -0.0256 1.0000 0.0845
-3.750 -0.3333 0.02323 0.01130 -0.0241 1.0000 0.0864
-3.500 -0.3147 0.02247 0.01046 -0.0228 1.0000 0.0889
-3.250 -0.2955 0.02182 0.00970 -0.0217 1.0000 0.0919
-3.000 -0.2762 0.02128 0.00903 -0.0207 1.0000 0.0971
-2.750 -0.2565 0.02069 0.00838 -0.0199 1.0000 0.1057
-2.500 -0.2363 0.02011 0.00784 -0.0192 1.0000 0.1200
-2.250 -0.2168 0.01816 0.00723 -0.0196 1.0000 0.3375
-2.000 -0.2093 0.01737 0.00777 -0.0150 1.0000 0.6454
-1.750 -0.1978 0.01740 0.00797 -0.0111 1.0000 0.7268
-1.500 -0.1753 0.01760 0.00826 -0.0087 0.9896 0.8109
-1.250 -0.1431 0.01774 0.00827 -0.0092 0.9797 0.8494
-1.000 -0.1079 0.01786 0.00828 -0.0103 0.9710 0.8882
-0.750 -0.0652 0.01798 0.00823 -0.0135 0.9632 0.9100
-0.500 -0.0221 0.01806 0.00815 -0.0169 0.9546 0.9339
-0.250 0.0551 0.01808 0.00808 -0.0266 0.9531 1.0000
0.000 0.0879 0.01819 0.00807 -0.0287 0.9417 1.0000
0.250 0.1228 0.01833 0.00812 -0.0311 0.9316 1.0000
0.500 0.1597 0.01848 0.00821 -0.0337 0.9223 1.0000
0.750 0.1905 0.01866 0.00835 -0.0351 0.9112 1.0000
1.000 0.2220 0.01886 0.00855 -0.0366 0.9011 1.0000
1.250 0.2581 0.01906 0.00875 -0.0386 0.8928 1.0000
1.500 0.2853 0.01931 0.00903 -0.0392 0.8816 1.0000
1.750 0.3142 0.01958 0.00936 -0.0399 0.8712 1.0000
2.000 0.3471 0.01982 0.00968 -0.0412 0.8627 1.0000
2.250 0.3745 0.02013 0.01007 -0.0415 0.8520 1.0000
2.500 0.4016 0.02046 0.01055 -0.0418 0.8413 1.0000
2.750 0.4317 0.02074 0.01098 -0.0424 0.8313 1.0000
3.000 0.4631 0.02098 0.01140 -0.0430 0.8210 1.0000
3.250 0.4898 0.02127 0.01188 -0.0428 0.8082 1.0000
3.500 0.5171 0.02154 0.01242 -0.0426 0.7950 1.0000
3.750 0.5463 0.02162 0.01276 -0.0422 0.7794 1.0000
4.000 0.5751 0.02054 0.01186 -0.0385 0.7359 1.0000
4.250 0.5914 0.01909 0.01017 -0.0314 0.6361 1.0000
4.500 0.6076 0.01899 0.00980 -0.0273 0.5129 1.0000
4.750 0.6121 0.02111 0.01011 -0.0231 0.2130 1.0000
5.000 0.6233 0.02359 0.01177 -0.0216 0.1201 1.0000
5.250 0.6407 0.02518 0.01320 -0.0204 0.0942 1.0000
5.500 0.6597 0.02665 0.01473 -0.0192 0.0837 1.0000
5.750 0.6798 0.02819 0.01624 -0.0181 0.0749 1.0000
6.000 0.7036 0.02949 0.01777 -0.0173 0.0658 1.0000
6.250 0.7305 0.03134 0.01961 -0.0168 0.0616 1.0000
6.500 0.7611 0.03329 0.02186 -0.0163 0.0584 1.0000
6.750 0.7880 0.03528 0.02413 -0.0160 0.0539 1.0000
7.000 0.8118 0.03768 0.02656 -0.0158 0.0499 1.0000
7.250 0.8358 0.04050 0.02981 -0.0151 0.0484 1.0000
7.500 0.8567 0.04357 0.03341 -0.0142 0.0476 1.0000
7.750 0.8739 0.04695 0.03731 -0.0131 0.0470 1.0000
8.000 0.8873 0.05058 0.04146 -0.0119 0.0466 1.0000
8.250 0.8966 0.05437 0.04578 -0.0106 0.0461 1.0000
8.500 0.9013 0.05823 0.05011 -0.0094 0.0451 1.0000
8.750 0.9021 0.06214 0.05442 -0.0083 0.0441 1.0000
9.000 0.8989 0.06612 0.05874 -0.0074 0.0433 1.0000
9.250 0.8915 0.07021 0.06310 -0.0067 0.0428 1.0000
9.500 0.8787 0.07434 0.06744 -0.0061 0.0428 1.0000
9.750 0.8610 0.07871 0.07195 -0.0063 0.0431 1.0000
10.000 0.8423 0.08378 0.07713 -0.0081 0.0437 1.0000
10.250 0.8240 0.08978 0.08320 -0.0116 0.0443 1.0000
10.500 0.8086 0.09658 0.09002 -0.0161 0.0451 1.0000
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Polar data table (+)
Polar graphs
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