NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-206 (naca64206-il) Reynolds number: 200,000 Max Cl/Cd: 56.17 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64206-il-200000.txt Download as CSV file: xf-naca64206-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-206
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5472 0.09001 0.08653 -0.0076 1.0000 0.0268
-8.000 -0.5465 0.08618 0.08276 -0.0104 1.0000 0.0275
-7.750 -0.5483 0.08214 0.07879 -0.0163 1.0000 0.0287
-7.500 -0.5424 0.07733 0.07393 -0.0234 1.0000 0.0291
-6.750 -0.5271 0.06145 0.05778 -0.0330 1.0000 0.0310
-6.500 -0.5188 0.05799 0.05432 -0.0326 1.0000 0.0328
-6.250 -0.5065 0.05428 0.05052 -0.0337 1.0000 0.0345
-6.000 -0.4917 0.05043 0.04651 -0.0351 1.0000 0.0366
-5.750 -0.4733 0.04657 0.04239 -0.0363 1.0000 0.0397
-5.500 -0.4460 0.04623 0.04131 -0.0364 1.0000 0.0427
-5.250 -0.4359 0.03859 0.03376 -0.0376 1.0000 0.0450
-5.000 -0.4176 0.03572 0.03082 -0.0375 1.0000 0.0480
-4.500 -0.3749 0.03010 0.02462 -0.0371 1.0000 0.0603
-4.250 -0.3525 0.02784 0.02200 -0.0368 1.0000 0.0718
-4.000 -0.3307 0.02569 0.01966 -0.0364 1.0000 0.0853
-3.750 -0.2966 0.02131 0.01452 -0.0337 1.0000 0.0395
-3.500 -0.2715 0.01913 0.01194 -0.0327 1.0000 0.0396
-3.250 -0.2465 0.01717 0.00971 -0.0316 1.0000 0.0389
-3.000 -0.2217 0.01539 0.00771 -0.0304 1.0000 0.0371
-2.750 -0.1977 0.01407 0.00629 -0.0294 1.0000 0.0378
-2.500 -0.1740 0.01305 0.00521 -0.0284 1.0000 0.0406
-2.250 -0.1506 0.01206 0.00424 -0.0278 1.0000 0.0481
-2.000 -0.1265 0.01138 0.00352 -0.0272 1.0000 0.0544
-1.750 -0.1004 0.01010 0.00259 -0.0273 1.0000 0.1555
-1.500 -0.0929 0.00783 0.00289 -0.0230 1.0000 0.8167
-1.250 -0.0877 0.00772 0.00299 -0.0172 1.0000 0.9207
-1.000 -0.0499 0.00761 0.00277 -0.0195 1.0000 1.0000
-0.750 -0.0261 0.00771 0.00274 -0.0196 1.0000 1.0000
-0.500 0.0072 0.00785 0.00276 -0.0214 0.9968 1.0000
-0.250 0.0501 0.00799 0.00279 -0.0251 0.9898 1.0000
0.000 0.0940 0.00813 0.00286 -0.0288 0.9831 1.0000
0.250 0.1351 0.00821 0.00291 -0.0320 0.9752 1.0000
0.500 0.1799 0.00828 0.00298 -0.0358 0.9692 1.0000
0.750 0.2204 0.00831 0.00304 -0.0387 0.9607 1.0000
1.000 0.2663 0.00832 0.00310 -0.0426 0.9553 1.0000
1.250 0.3042 0.00833 0.00317 -0.0448 0.9453 1.0000
1.500 0.3421 0.00833 0.00325 -0.0469 0.9350 1.0000
1.750 0.3774 0.00826 0.00334 -0.0480 0.9207 1.0000
2.000 0.4047 0.00802 0.00312 -0.0463 0.8895 1.0000
2.250 0.4223 0.00783 0.00282 -0.0422 0.8315 1.0000
2.500 0.4432 0.00789 0.00275 -0.0397 0.7713 1.0000
2.750 0.4621 0.00825 0.00267 -0.0368 0.6518 1.0000
3.000 0.4654 0.01185 0.00348 -0.0331 0.0734 1.0000
3.250 0.4900 0.01285 0.00444 -0.0325 0.0487 1.0000
3.500 0.5140 0.01396 0.00566 -0.0318 0.0422 1.0000
3.750 0.5385 0.01512 0.00686 -0.0310 0.0383 1.0000
4.000 0.5635 0.01657 0.00834 -0.0302 0.0366 1.0000
4.250 0.5889 0.01865 0.01045 -0.0296 0.0342 1.0000
4.500 0.6156 0.02064 0.01271 -0.0289 0.0315 1.0000
4.750 0.6423 0.02350 0.01587 -0.0281 0.0320 1.0000
5.750 0.7448 0.03778 0.03229 -0.0221 0.0542 1.0000
6.000 0.7641 0.04062 0.03525 -0.0217 0.0480 1.0000
6.250 0.7739 0.04887 0.04355 -0.0222 0.0455 1.0000
6.500 0.7952 0.04850 0.04400 -0.0201 0.0391 1.0000
6.750 0.8089 0.05214 0.04785 -0.0198 0.0366 1.0000
7.000 0.8208 0.05601 0.05178 -0.0197 0.0349 1.0000
7.250 0.8254 0.06350 0.05925 -0.0204 0.0334 1.0000
7.500 0.8254 0.07004 0.06604 -0.0207 0.0330 1.0000
7.750 0.8286 0.07380 0.07007 -0.0207 0.0328 1.0000
8.000 0.8292 0.07725 0.07377 -0.0211 0.0325 1.0000
8.250 0.8241 0.08122 0.07794 -0.0226 0.0320 1.0000
8.500 0.8145 0.08555 0.08238 -0.0244 0.0317 1.0000
8.750 0.8037 0.09055 0.08741 -0.0277 0.0317 1.0000
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Polar data table (+)
Polar graphs
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