NACA 1408 (naca1408-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1408 (naca1408-il) Reynolds number: 50,000 Max Cl/Cd: 31.5 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1408-il-50000-n5.txt Download as CSV file: xf-naca1408-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1408
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6252 0.10687 0.09980 -0.0050 1.0000 0.0513
-9.750 -0.6249 0.10194 0.09491 -0.0071 1.0000 0.0511
-9.500 -0.6252 0.09694 0.08995 -0.0094 1.0000 0.0509
-9.250 -0.6266 0.09169 0.08470 -0.0123 1.0000 0.0506
-9.000 -0.6298 0.08595 0.07900 -0.0162 1.0000 0.0502
-8.750 -0.6359 0.08001 0.07315 -0.0205 1.0000 0.0498
-8.500 -0.6417 0.07420 0.06729 -0.0240 1.0000 0.0495
-8.250 -0.6469 0.06849 0.06145 -0.0269 1.0000 0.0493
-8.000 -0.6498 0.06289 0.05564 -0.0290 1.0000 0.0493
-7.750 -0.6501 0.05740 0.04978 -0.0304 1.0000 0.0499
-7.500 -0.6472 0.05208 0.04389 -0.0312 1.0000 0.0510
-7.250 -0.6366 0.04844 0.04002 -0.0310 1.0000 0.0533
-7.000 -0.6222 0.04537 0.03670 -0.0306 1.0000 0.0556
-6.750 -0.6075 0.04164 0.03250 -0.0301 1.0000 0.0574
-6.500 -0.5905 0.03837 0.02866 -0.0294 1.0000 0.0614
-6.250 -0.5715 0.03532 0.02500 -0.0286 1.0000 0.0657
-6.000 -0.5505 0.03302 0.02250 -0.0279 1.0000 0.0693
-5.750 -0.5282 0.03104 0.02010 -0.0270 1.0000 0.0758
-5.500 -0.5056 0.02918 0.01803 -0.0263 1.0000 0.0820
-5.250 -0.4817 0.02746 0.01603 -0.0253 1.0000 0.0871
-5.000 -0.4574 0.02591 0.01423 -0.0243 1.0000 0.0933
-4.750 -0.4342 0.02480 0.01302 -0.0235 1.0000 0.1046
-4.500 -0.4108 0.02358 0.01179 -0.0226 1.0000 0.1142
-4.250 -0.3870 0.02243 0.01054 -0.0217 1.0000 0.1264
-4.000 -0.3628 0.02133 0.00942 -0.0210 1.0000 0.1476
-3.750 -0.3403 0.02024 0.00856 -0.0204 1.0000 0.1898
-3.500 -0.3189 0.01912 0.00788 -0.0196 1.0000 0.2680
-3.000 -0.2822 0.01702 0.00714 -0.0160 1.0000 0.5337
-2.750 -0.2650 0.01635 0.00702 -0.0127 1.0000 0.6734
-2.500 -0.2388 0.01599 0.00697 -0.0102 1.0000 0.8165
-2.250 -0.1788 0.01591 0.00667 -0.0150 1.0000 0.9424
-2.000 -0.1158 0.01576 0.00613 -0.0223 1.0000 1.0000
-1.750 -0.1017 0.01564 0.00581 -0.0204 1.0000 1.0000
-1.500 -0.0865 0.01557 0.00557 -0.0186 1.0000 1.0000
-1.250 -0.0702 0.01555 0.00538 -0.0169 1.0000 1.0000
-1.000 -0.0528 0.01556 0.00526 -0.0154 1.0000 1.0000
-0.750 -0.0347 0.01561 0.00517 -0.0141 1.0000 1.0000
-0.500 -0.0160 0.01568 0.00514 -0.0128 1.0000 1.0000
-0.250 0.0032 0.01580 0.00517 -0.0117 1.0000 1.0000
0.000 0.0227 0.01595 0.00525 -0.0108 1.0000 1.0000
0.250 0.0424 0.01613 0.00537 -0.0099 1.0000 1.0000
0.500 0.0622 0.01636 0.00556 -0.0091 1.0000 1.0000
0.750 0.0864 0.01664 0.00583 -0.0093 0.9975 1.0000
1.000 0.1335 0.01696 0.00617 -0.0139 0.9820 1.0000
1.250 0.1802 0.01723 0.00649 -0.0182 0.9656 1.0000
1.500 0.2260 0.01745 0.00681 -0.0221 0.9482 1.0000
1.750 0.2704 0.01762 0.00709 -0.0256 0.9291 1.0000
2.000 0.3146 0.01772 0.00736 -0.0287 0.9095 1.0000
2.250 0.3534 0.01779 0.00757 -0.0306 0.8863 1.0000
2.500 0.3913 0.01781 0.00775 -0.0320 0.8619 1.0000
2.750 0.4257 0.01782 0.00794 -0.0325 0.8348 1.0000
3.000 0.4567 0.01785 0.00810 -0.0322 0.8043 1.0000
3.250 0.4855 0.01790 0.00826 -0.0313 0.7703 1.0000
3.500 0.5129 0.01795 0.00841 -0.0300 0.7332 1.0000
3.750 0.5377 0.01807 0.00856 -0.0282 0.6903 1.0000
4.000 0.5603 0.01827 0.00873 -0.0260 0.6383 1.0000
4.250 0.5813 0.01857 0.00891 -0.0235 0.5765 1.0000
4.500 0.5997 0.01904 0.00910 -0.0208 0.4947 1.0000
4.750 0.6164 0.01981 0.00940 -0.0183 0.3895 1.0000
5.000 0.6339 0.02098 0.01000 -0.0167 0.2753 1.0000
5.250 0.6518 0.02263 0.01106 -0.0156 0.1794 1.0000
5.500 0.6718 0.02424 0.01236 -0.0147 0.1344 1.0000
5.750 0.6929 0.02570 0.01377 -0.0138 0.1151 1.0000
6.000 0.7148 0.02712 0.01528 -0.0127 0.1037 1.0000
6.250 0.7375 0.02865 0.01688 -0.0116 0.0958 1.0000
6.500 0.7598 0.03011 0.01843 -0.0108 0.0861 1.0000
6.750 0.7840 0.03180 0.02040 -0.0099 0.0789 1.0000
7.000 0.8077 0.03374 0.02245 -0.0091 0.0736 1.0000
7.250 0.8300 0.03587 0.02490 -0.0083 0.0670 1.0000
7.500 0.8514 0.03817 0.02751 -0.0074 0.0620 1.0000
7.750 0.8709 0.04095 0.03033 -0.0067 0.0583 1.0000
8.000 0.8865 0.04394 0.03410 -0.0052 0.0542 1.0000
8.250 0.8998 0.04729 0.03795 -0.0040 0.0514 1.0000
8.500 0.9104 0.05090 0.04205 -0.0028 0.0497 1.0000
8.750 0.9199 0.05410 0.04551 -0.0018 0.0476 1.0000
9.000 0.9259 0.05788 0.04940 -0.0009 0.0457 1.0000
9.250 0.9206 0.06231 0.05440 0.0003 0.0448 1.0000
9.500 0.9110 0.06696 0.05946 0.0010 0.0443 1.0000
9.750 0.8974 0.07168 0.06447 0.0012 0.0441 1.0000
10.000 0.8796 0.07631 0.06927 0.0011 0.0442 1.0000
10.250 0.8614 0.08164 0.07471 -0.0010 0.0445 1.0000
10.500 0.8442 0.08790 0.08104 -0.0049 0.0448 1.0000
10.750 0.8295 0.09495 0.08812 -0.0098 0.0451 1.0000
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Polar data table (+)
Polar graphs
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