NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-206 (naca65206-il) Reynolds number: 50,000 Max Cl/Cd: 29.4 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65206-il-50000-n5.txt Download as CSV file: xf-naca65206-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-206
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5608 0.09441 0.08774 -0.0112 1.0000 0.1053
-7.750 -0.5583 0.09086 0.08425 -0.0127 1.0000 0.1092
-7.500 -0.5731 0.08792 0.08130 -0.0238 1.0000 0.1151
-6.500 -0.5211 0.06675 0.05975 -0.0317 1.0000 0.0591
-6.250 -0.5099 0.06232 0.05526 -0.0326 1.0000 0.0566
-6.000 -0.4912 0.05797 0.05030 -0.0352 1.0000 0.0471
-5.750 -0.4769 0.05363 0.04583 -0.0355 1.0000 0.0463
-5.500 -0.4611 0.04958 0.04159 -0.0358 1.0000 0.0450
-5.250 -0.4431 0.04567 0.03739 -0.0361 1.0000 0.0431
-5.000 -0.4229 0.04196 0.03329 -0.0361 1.0000 0.0414
-4.750 -0.4009 0.03850 0.02936 -0.0359 1.0000 0.0401
-4.500 -0.3777 0.03532 0.02567 -0.0354 1.0000 0.0395
-4.250 -0.3537 0.03246 0.02233 -0.0347 1.0000 0.0396
-4.000 -0.3293 0.02995 0.01937 -0.0339 1.0000 0.0408
-3.750 -0.3038 0.02830 0.01708 -0.0329 1.0000 0.0472
-3.500 -0.2801 0.02582 0.01444 -0.0320 1.0000 0.0503
-3.250 -0.2559 0.02397 0.01226 -0.0305 1.0000 0.0526
-3.000 -0.2326 0.02248 0.01057 -0.0289 1.0000 0.0558
-2.750 -0.2096 0.02131 0.00911 -0.0274 1.0000 0.0598
-2.500 -0.1875 0.02022 0.00790 -0.0265 1.0000 0.0732
-2.250 -0.1648 0.01914 0.00675 -0.0258 1.0000 0.0899
-2.000 -0.1409 0.01785 0.00564 -0.0254 1.0000 0.1310
-1.750 -0.1078 0.01461 0.00543 -0.0223 1.0000 1.0000
-1.500 -0.0913 0.01454 0.00488 -0.0207 1.0000 1.0000
-1.250 -0.0729 0.01452 0.00453 -0.0195 1.0000 1.0000
-1.000 -0.0533 0.01453 0.00427 -0.0186 1.0000 1.0000
-0.750 -0.0328 0.01457 0.00407 -0.0178 1.0000 1.0000
-0.500 -0.0118 0.01465 0.00395 -0.0172 1.0000 1.0000
-0.250 0.0095 0.01475 0.00389 -0.0166 1.0000 1.0000
0.000 0.0311 0.01488 0.00385 -0.0161 1.0000 1.0000
0.250 0.0527 0.01504 0.00390 -0.0156 1.0000 1.0000
0.500 0.0743 0.01522 0.00401 -0.0151 1.0000 1.0000
0.750 0.0958 0.01544 0.00417 -0.0147 1.0000 1.0000
1.000 0.1173 0.01568 0.00440 -0.0143 1.0000 1.0000
1.250 0.1387 0.01595 0.00470 -0.0140 1.0000 1.0000
1.500 0.1642 0.01629 0.00507 -0.0145 0.9973 1.0000
1.750 0.2022 0.01673 0.00562 -0.0174 0.9879 1.0000
2.000 0.2403 0.01717 0.00621 -0.0203 0.9783 1.0000
2.250 0.2779 0.01760 0.00685 -0.0231 0.9680 1.0000
2.500 0.3151 0.01802 0.00763 -0.0256 0.9570 1.0000
2.750 0.3523 0.01844 0.00837 -0.0281 0.9452 1.0000
3.000 0.3909 0.01884 0.00921 -0.0306 0.9325 1.0000
3.250 0.4830 0.01643 0.00684 -0.0298 0.5529 1.0000
3.500 0.4840 0.02040 0.00778 -0.0259 0.0993 1.0000
3.750 0.5062 0.02187 0.00921 -0.0251 0.0743 1.0000
4.000 0.5288 0.02330 0.01079 -0.0242 0.0657 1.0000
4.250 0.5534 0.02480 0.01258 -0.0231 0.0609 1.0000
4.500 0.5813 0.02658 0.01460 -0.0221 0.0567 1.0000
4.750 0.6089 0.02860 0.01680 -0.0216 0.0477 1.0000
5.000 0.6370 0.03086 0.01935 -0.0209 0.0429 1.0000
5.250 0.6641 0.03372 0.02272 -0.0202 0.0410 1.0000
5.500 0.6890 0.03706 0.02645 -0.0195 0.0399 1.0000
5.750 0.7114 0.04078 0.03064 -0.0185 0.0394 1.0000
6.000 0.7309 0.04438 0.03481 -0.0174 0.0380 1.0000
6.250 0.7493 0.04757 0.03873 -0.0161 0.0355 1.0000
6.500 0.7644 0.05136 0.04308 -0.0152 0.0337 1.0000
6.750 0.7769 0.05560 0.04775 -0.0144 0.0339 1.0000
7.000 0.7868 0.05999 0.05252 -0.0140 0.0345 1.0000
7.250 0.7938 0.06456 0.05740 -0.0137 0.0351 1.0000
7.500 0.7984 0.06913 0.06221 -0.0138 0.0359 1.0000
7.750 0.8011 0.07373 0.06698 -0.0140 0.0367 1.0000
8.000 0.8024 0.07856 0.07191 -0.0144 0.0376 1.0000
8.250 0.8010 0.08298 0.07659 -0.0156 0.0410 1.0000
8.500 0.7895 0.08813 0.08185 -0.0182 0.0431 1.0000
8.750 0.7807 0.09328 0.08700 -0.0213 0.0447 1.0000
9.000 0.7754 0.09891 0.09260 -0.0254 0.0466 1.0000
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Polar data table (+)
Polar graphs
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