NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-210 (naca65210-il) Reynolds number: 50,000 Max Cl/Cd: 29.67 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65210-il-50000-n5.txt Download as CSV file: xf-naca65210-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-210
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5343 0.11197 0.10475 -0.0225 1.0000 0.0765
-10.250 -0.5388 0.10536 0.09820 -0.0270 1.0000 0.0638
-10.000 -0.5328 0.10122 0.09407 -0.0274 1.0000 0.0611
-9.750 -0.5340 0.09627 0.08918 -0.0298 1.0000 0.0586
-9.250 -0.5823 0.08265 0.07562 -0.0434 1.0000 0.0519
-8.750 -0.5843 0.07475 0.06769 -0.0436 1.0000 0.0507
-8.500 -0.5896 0.07082 0.06371 -0.0438 1.0000 0.0501
-8.250 -0.5943 0.06699 0.05977 -0.0437 1.0000 0.0496
-8.000 -0.5978 0.06319 0.05582 -0.0432 1.0000 0.0490
-7.750 -0.5991 0.05954 0.05198 -0.0423 1.0000 0.0486
-7.500 -0.5985 0.05599 0.04818 -0.0411 1.0000 0.0482
-7.250 -0.5960 0.05255 0.04446 -0.0395 1.0000 0.0479
-7.000 -0.5913 0.04936 0.04094 -0.0378 1.0000 0.0480
-6.750 -0.5847 0.04643 0.03760 -0.0359 1.0000 0.0492
-6.500 -0.5759 0.04381 0.03446 -0.0338 1.0000 0.0509
-6.250 -0.5644 0.04139 0.03154 -0.0317 1.0000 0.0518
-6.000 -0.5506 0.03891 0.02868 -0.0299 1.0000 0.0521
-5.750 -0.5353 0.03625 0.02575 -0.0283 1.0000 0.0528
-5.500 -0.5184 0.03404 0.02330 -0.0268 1.0000 0.0538
-5.250 -0.5004 0.03221 0.02122 -0.0253 1.0000 0.0555
-5.000 -0.4823 0.03077 0.01962 -0.0239 1.0000 0.0592
-4.750 -0.4625 0.02944 0.01801 -0.0223 1.0000 0.0629
-4.500 -0.4418 0.02820 0.01652 -0.0206 1.0000 0.0648
-4.250 -0.4225 0.02691 0.01523 -0.0188 1.0000 0.0673
-4.000 -0.4047 0.02594 0.01420 -0.0171 1.0000 0.0710
-3.750 -0.3873 0.02522 0.01324 -0.0154 1.0000 0.0783
-3.500 -0.3708 0.02430 0.01234 -0.0140 1.0000 0.0856
-3.250 -0.3530 0.02354 0.01143 -0.0126 1.0000 0.0933
-3.000 -0.3270 0.02253 0.01046 -0.0133 0.9964 0.1120
-2.750 -0.3095 0.01928 0.00982 -0.0133 0.9910 0.5009
-2.500 -0.2964 0.01964 0.01075 -0.0073 0.9831 0.7464
-2.250 -0.2841 0.02055 0.01175 -0.0001 0.9760 0.8477
-2.000 -0.2357 0.02149 0.01243 0.0005 0.9760 0.9255
-1.750 -0.1930 0.02143 0.01202 -0.0032 0.9704 0.9357
-1.500 -0.1466 0.02141 0.01166 -0.0077 0.9656 0.9443
-1.250 -0.1035 0.02137 0.01139 -0.0118 0.9602 0.9535
-1.000 -0.0569 0.02135 0.01114 -0.0165 0.9551 0.9614
-0.750 -0.0081 0.02136 0.01098 -0.0217 0.9509 0.9687
-0.500 0.0336 0.02133 0.01084 -0.0256 0.9445 0.9774
-0.250 0.0794 0.02135 0.01076 -0.0302 0.9394 0.9857
0.000 0.1243 0.02137 0.01072 -0.0347 0.9341 0.9942
0.250 0.1580 0.02144 0.01076 -0.0372 0.9268 1.0000
0.500 0.1832 0.02155 0.01086 -0.0379 0.9184 1.0000
0.750 0.2092 0.02168 0.01099 -0.0387 0.9104 1.0000
1.000 0.2277 0.02185 0.01117 -0.0381 0.9009 1.0000
1.250 0.2582 0.02201 0.01137 -0.0395 0.8944 1.0000
1.500 0.2722 0.02224 0.01164 -0.0379 0.8842 1.0000
1.750 0.2944 0.02248 0.01191 -0.0377 0.8761 1.0000
2.000 0.3174 0.02273 0.01223 -0.0375 0.8679 1.0000
2.250 0.3369 0.02305 0.01261 -0.0367 0.8589 1.0000
2.500 0.3671 0.02332 0.01302 -0.0377 0.8522 1.0000
2.750 0.3861 0.02370 0.01350 -0.0368 0.8423 1.0000
3.000 0.4172 0.02398 0.01394 -0.0377 0.8352 1.0000
3.250 0.4407 0.02434 0.01445 -0.0373 0.8251 1.0000
3.500 0.4649 0.02468 0.01502 -0.0370 0.8147 1.0000
3.750 0.4957 0.02490 0.01549 -0.0375 0.8051 1.0000
4.000 0.5271 0.02503 0.01592 -0.0378 0.7942 1.0000
4.250 0.5706 0.02270 0.01395 -0.0348 0.7420 1.0000
4.500 0.5924 0.02022 0.01134 -0.0274 0.6286 1.0000
4.750 0.6037 0.02035 0.01015 -0.0214 0.3509 1.0000
5.000 0.5999 0.02326 0.01150 -0.0176 0.1440 1.0000
5.250 0.6111 0.02505 0.01290 -0.0157 0.1043 1.0000
5.500 0.6263 0.02643 0.01420 -0.0142 0.0874 1.0000
5.750 0.6434 0.02777 0.01566 -0.0127 0.0796 1.0000
6.000 0.6631 0.02911 0.01707 -0.0115 0.0733 1.0000
6.250 0.6879 0.03048 0.01857 -0.0109 0.0662 1.0000
6.500 0.7171 0.03197 0.02016 -0.0107 0.0606 1.0000
6.750 0.7528 0.03418 0.02237 -0.0114 0.0577 1.0000
7.000 0.7846 0.03633 0.02494 -0.0114 0.0554 1.0000
7.250 0.8105 0.03850 0.02749 -0.0110 0.0519 1.0000
7.500 0.8334 0.04081 0.03005 -0.0105 0.0488 1.0000
7.750 0.8550 0.04362 0.03319 -0.0098 0.0477 1.0000
8.000 0.8733 0.04675 0.03667 -0.0090 0.0469 1.0000
8.250 0.8883 0.05018 0.04047 -0.0079 0.0464 1.0000
8.500 0.8997 0.05378 0.04446 -0.0066 0.0462 1.0000
8.750 0.9075 0.05784 0.04892 -0.0053 0.0457 1.0000
9.000 0.9086 0.06128 0.05280 -0.0034 0.0452 1.0000
9.250 0.9055 0.06479 0.05676 -0.0015 0.0447 1.0000
9.500 0.8984 0.06845 0.06077 0.0002 0.0442 1.0000
9.750 0.8882 0.07219 0.06480 0.0017 0.0440 1.0000
10.000 0.8723 0.07582 0.06863 0.0032 0.0439 1.0000
10.250 0.8560 0.07981 0.07277 0.0036 0.0440 1.0000
10.500 0.8401 0.08424 0.07732 0.0029 0.0442 1.0000
10.750 0.8236 0.08929 0.08246 0.0011 0.0444 1.0000
11.000 0.8086 0.09486 0.08810 -0.0017 0.0447 1.0000
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Polar data table (+)
Polar graphs
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