NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M14 AIRFOIL (m14-il) Reynolds number: 50,000 Max Cl/Cd: 38.85 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m14-il-50000-n5.txt Download as CSV file: xf-m14-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M14 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3153 0.11383 0.10730 -0.0198 1.0000 0.0975
-9.500 -0.3224 0.11206 0.10560 -0.0218 1.0000 0.0996
-9.250 -0.4189 0.11768 0.11078 -0.0106 1.0000 0.0904
-9.000 -0.4134 0.11450 0.10763 -0.0117 1.0000 0.0949
-8.750 -0.4148 0.11237 0.10558 -0.0145 1.0000 0.0988
-8.500 -0.4223 0.11107 0.10440 -0.0188 1.0000 0.1001
-8.250 -0.4283 0.10941 0.10284 -0.0242 1.0000 0.1006
-8.000 -0.4006 0.10168 0.09505 -0.0179 1.0000 0.1050
-7.750 -0.3962 0.09851 0.09194 -0.0188 1.0000 0.1084
-7.500 -0.3958 0.09580 0.08931 -0.0216 1.0000 0.1123
-7.250 -0.3985 0.09414 0.08769 -0.0294 1.0000 0.1150
-7.000 -0.3874 0.08901 0.08264 -0.0268 1.0000 0.1178
-6.750 -0.3785 0.08575 0.07938 -0.0265 1.0000 0.1249
-6.500 -0.3769 0.08396 0.07757 -0.0342 1.0000 0.1304
-6.250 -0.3663 0.07929 0.07300 -0.0299 1.0000 0.1348
-6.000 -0.3593 0.07643 0.07016 -0.0310 1.0000 0.1406
-5.500 -0.3480 0.07052 0.06429 -0.0319 1.0000 0.1495
-5.250 -0.3420 0.06932 0.06293 -0.0352 1.0000 0.1600
-5.000 -0.3386 0.06561 0.05935 -0.0321 1.0000 0.1623
-4.750 -0.3347 0.06339 0.05715 -0.0302 1.0000 0.1701
-4.250 -0.2570 0.05175 0.04434 -0.0434 0.9875 0.0842
-4.000 -0.2221 0.04780 0.04015 -0.0471 0.9776 0.0803
-3.750 -0.1836 0.04391 0.03581 -0.0512 0.9675 0.0765
-3.500 -0.1456 0.04089 0.03238 -0.0547 0.9575 0.0774
-3.250 -0.1047 0.03808 0.02912 -0.0583 0.9492 0.0789
-3.000 -0.0676 0.03543 0.02596 -0.0608 0.9386 0.0773
-2.750 -0.0293 0.03306 0.02308 -0.0631 0.9290 0.0760
-2.500 0.0105 0.03097 0.02050 -0.0654 0.9205 0.0754
-2.250 0.0450 0.02934 0.01848 -0.0667 0.9093 0.0754
-2.000 0.0800 0.02794 0.01671 -0.0679 0.8986 0.0759
-1.750 0.1162 0.02676 0.01524 -0.0693 0.8890 0.0779
-1.500 0.1500 0.02588 0.01409 -0.0701 0.8781 0.0827
-1.250 0.1826 0.02512 0.01302 -0.0705 0.8667 0.0860
-1.000 0.2156 0.02430 0.01208 -0.0711 0.8559 0.0885
-0.750 0.2474 0.02365 0.01130 -0.0714 0.8455 0.0919
-0.500 0.2765 0.02315 0.01066 -0.0712 0.8343 0.0964
-0.250 0.3034 0.02276 0.01017 -0.0708 0.8223 0.1025
0.000 0.3302 0.02242 0.00979 -0.0703 0.8108 0.1138
0.250 0.3571 0.02195 0.00947 -0.0699 0.8000 0.1457
0.750 0.4277 0.01967 0.00901 -0.0722 0.7784 1.0000
1.000 0.4528 0.01989 0.00900 -0.0714 0.7668 1.0000
1.250 0.4783 0.02010 0.00901 -0.0707 0.7559 1.0000
1.500 0.5038 0.02030 0.00905 -0.0700 0.7451 1.0000
1.750 0.5283 0.02059 0.00924 -0.0693 0.7332 1.0000
2.000 0.5533 0.02087 0.00941 -0.0687 0.7219 1.0000
2.250 0.5790 0.02111 0.00956 -0.0680 0.7117 1.0000
2.500 0.6043 0.02138 0.00978 -0.0674 0.7010 1.0000
2.750 0.6286 0.02173 0.01011 -0.0668 0.6895 1.0000
3.000 0.6536 0.02206 0.01041 -0.0662 0.6789 1.0000
3.250 0.6797 0.02228 0.01060 -0.0655 0.6697 1.0000
3.500 0.7036 0.02270 0.01108 -0.0649 0.6581 1.0000
3.750 0.7278 0.02310 0.01153 -0.0643 0.6472 1.0000
4.000 0.7531 0.02343 0.01189 -0.0637 0.6373 1.0000
4.250 0.7779 0.02379 0.01234 -0.0631 0.6272 1.0000
4.500 0.8016 0.02427 0.01292 -0.0625 0.6159 1.0000
4.750 0.8260 0.02470 0.01345 -0.0618 0.6057 1.0000
5.000 0.8517 0.02501 0.01387 -0.0612 0.5965 1.0000
5.250 0.8746 0.02557 0.01461 -0.0605 0.5849 1.0000
5.500 0.8982 0.02611 0.01530 -0.0599 0.5742 1.0000
5.750 0.9233 0.02649 0.01582 -0.0592 0.5646 1.0000
6.000 0.9469 0.02702 0.01658 -0.0585 0.5538 1.0000
6.250 0.9693 0.02764 0.01743 -0.0577 0.5422 1.0000
6.500 0.9925 0.02818 0.01820 -0.0569 0.5309 1.0000
6.750 1.0163 0.02857 0.01881 -0.0559 0.5191 1.0000
7.000 1.0398 0.02889 0.01940 -0.0548 0.5056 1.0000
7.250 1.0607 0.02919 0.01997 -0.0533 0.4880 1.0000
7.500 1.0791 0.02864 0.01954 -0.0505 0.4559 1.0000
7.750 1.0889 0.02803 0.01879 -0.0465 0.3972 1.0000
8.000 1.0948 0.02852 0.01899 -0.0430 0.3238 1.0000
8.250 1.0961 0.03011 0.02005 -0.0396 0.2188 1.0000
8.500 1.0857 0.03327 0.02237 -0.0362 0.1262 1.0000
8.750 1.0782 0.03636 0.02508 -0.0332 0.0909 1.0000
9.000 1.0724 0.03903 0.02764 -0.0304 0.0764 1.0000
9.250 1.0673 0.04185 0.03043 -0.0284 0.0681 1.0000
9.500 1.0659 0.04453 0.03323 -0.0268 0.0621 1.0000
9.750 1.0645 0.04734 0.03613 -0.0255 0.0583 1.0000
10.000 1.0621 0.05033 0.03916 -0.0244 0.0553 1.0000
10.250 1.0659 0.05277 0.04178 -0.0231 0.0519 1.0000
10.500 1.0714 0.05510 0.04427 -0.0218 0.0482 1.0000
10.750 1.0777 0.05738 0.04662 -0.0204 0.0451 1.0000
11.000 1.0950 0.05893 0.04816 -0.0178 0.0427 1.0000
11.250 1.1188 0.06044 0.05008 -0.0156 0.0406 1.0000
11.500 1.1343 0.06276 0.05270 -0.0142 0.0383 1.0000
11.750 1.1437 0.06548 0.05566 -0.0133 0.0364 1.0000
12.000 1.1506 0.06847 0.05884 -0.0125 0.0350 1.0000
12.250 1.1567 0.07185 0.06242 -0.0117 0.0342 1.0000
12.500 1.1592 0.07567 0.06648 -0.0112 0.0337 1.0000
12.750 1.1569 0.07995 0.07100 -0.0111 0.0333 1.0000
13.000 1.1487 0.08456 0.07582 -0.0115 0.0332 1.0000
13.250 1.1363 0.08952 0.08106 -0.0126 0.0332 1.0000
13.500 1.1225 0.09484 0.08662 -0.0142 0.0332 1.0000
14.000 1.0884 0.10699 0.09929 -0.0198 0.0334 1.0000
14.250 1.0656 0.11464 0.10719 -0.0245 0.0338 1.0000
14.500 1.0381 0.12441 0.11719 -0.0312 0.0345 1.0000
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Polar data table (+)
Polar graphs
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