NACA 16009 (naca16009-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 16009 (naca16009-il) Reynolds number: 200,000 Max Cl/Cd: 39.44 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16009-il-200000.txt Download as CSV file: xf-naca16009-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16009
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4953 0.09080 0.08740 -0.0314 1.0000 0.0445
-9.750 -0.5055 0.08570 0.08234 -0.0334 1.0000 0.0453
-9.500 -0.5182 0.08028 0.07695 -0.0359 1.0000 0.0456
-9.250 -0.5343 0.07456 0.07126 -0.0387 1.0000 0.0452
-7.000 -0.7006 0.04553 0.04115 -0.0072 1.0000 0.0487
-6.750 -0.6961 0.03992 0.03572 -0.0061 1.0000 0.0507
-6.500 -0.6934 0.03709 0.03279 -0.0032 1.0000 0.0525
-6.250 -0.6910 0.03440 0.02993 0.0002 1.0000 0.0552
-5.000 -0.6634 0.02821 0.02112 0.0205 1.0000 0.0322
-4.750 -0.6409 0.02445 0.01673 0.0229 1.0000 0.0278
-4.500 -0.6156 0.02210 0.01400 0.0244 1.0000 0.0269
-4.250 -0.5911 0.02047 0.01217 0.0254 1.0000 0.0281
-4.000 -0.5690 0.01971 0.01131 0.0265 1.0000 0.0326
-3.750 -0.5453 0.01842 0.00989 0.0277 1.0000 0.0341
-3.500 -0.5236 0.01734 0.00868 0.0292 1.0000 0.0361
-3.250 -0.5050 0.01602 0.00738 0.0310 1.0000 0.0427
-3.000 -0.4854 0.01516 0.00653 0.0326 1.0000 0.0632
-2.750 -0.4726 0.01287 0.00559 0.0348 1.0000 0.3155
-2.500 -0.4521 0.01146 0.00669 0.0389 1.0000 0.8992
-2.250 -0.3705 0.01320 0.00807 0.0299 1.0000 0.9509
-2.000 -0.2084 0.01478 0.00921 0.0036 1.0000 0.9794
-1.750 -0.1164 0.01481 0.00902 -0.0100 1.0000 0.9930
-1.500 -0.0698 0.01460 0.00872 -0.0147 1.0000 0.9982
-1.250 -0.0469 0.01446 0.00854 -0.0146 1.0000 1.0000
-1.000 -0.0373 0.01438 0.00843 -0.0117 1.0000 1.0000
-0.750 -0.0278 0.01431 0.00834 -0.0088 1.0000 1.0000
-0.500 -0.0185 0.01426 0.00827 -0.0059 1.0000 1.0000
-0.250 -0.0092 0.01424 0.00824 -0.0030 1.0000 1.0000
0.000 0.0000 0.01423 0.00823 0.0000 1.0000 1.0000
0.250 0.0092 0.01423 0.00824 0.0030 1.0000 1.0000
0.500 0.0185 0.01426 0.00827 0.0059 1.0000 1.0000
0.750 0.0278 0.01431 0.00833 0.0088 1.0000 1.0000
1.000 0.0373 0.01437 0.00843 0.0117 1.0000 1.0000
1.250 0.0469 0.01446 0.00853 0.0146 1.0000 1.0000
1.500 0.0697 0.01459 0.00871 0.0147 0.9983 1.0000
1.750 0.1163 0.01480 0.00901 0.0100 0.9931 1.0000
2.000 0.2085 0.01477 0.00921 -0.0036 0.9794 1.0000
2.250 0.3706 0.01319 0.00807 -0.0300 0.9509 1.0000
2.500 0.4520 0.01146 0.00668 -0.0388 0.8993 1.0000
2.750 0.4724 0.01287 0.00558 -0.0347 0.3151 1.0000
3.000 0.4853 0.01515 0.00652 -0.0326 0.0632 1.0000
3.250 0.5049 0.01601 0.00737 -0.0310 0.0428 1.0000
3.500 0.5235 0.01732 0.00866 -0.0291 0.0361 1.0000
3.750 0.5451 0.01842 0.00989 -0.0277 0.0341 1.0000
4.000 0.5688 0.01970 0.01129 -0.0265 0.0325 1.0000
4.250 0.5910 0.02047 0.01218 -0.0254 0.0281 1.0000
4.500 0.6155 0.02209 0.01398 -0.0243 0.0269 1.0000
4.750 0.6408 0.02443 0.01671 -0.0229 0.0278 1.0000
5.000 0.6633 0.02819 0.02109 -0.0205 0.0321 1.0000
7.000 0.7299 0.05912 0.05430 0.0052 0.0481 1.0000
7.250 0.7238 0.05778 0.05366 0.0122 0.0449 1.0000
7.500 0.7204 0.06042 0.05649 0.0159 0.0417 1.0000
7.750 0.7189 0.06264 0.05876 0.0191 0.0390 1.0000
8.000 0.7190 0.06508 0.06118 0.0217 0.0375 1.0000
8.250 0.7183 0.06942 0.06543 0.0236 0.0365 1.0000
8.500 0.6978 0.07622 0.07226 0.0266 0.0358 1.0000
8.750 0.6852 0.07892 0.07508 0.0302 0.0357 1.0000
9.000 0.6709 0.08162 0.07788 0.0335 0.0357 1.0000
9.250 0.6537 0.08411 0.08042 0.0370 0.0357 1.0000
9.500 0.6358 0.08687 0.08323 0.0394 0.0356 1.0000
9.750 0.6208 0.09047 0.08687 0.0395 0.0356 1.0000
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Polar data table (+)
Polar graphs
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